SCIENTIFIC ABSTRACT CARAFOLI, E. - CARAMAN, P.

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• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000308010012-6
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: June 12, 2000
• Sequence Number: 12
• Publication Date: December 31, 1967
• Content Type: SCIENCEAB

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21

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JI~iete (Aberdeen, Md.).

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so
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-rttix~ at tlie--
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n.urnber M. Lef.-
VC,
IX
e nen
0 A~iL!r~w -~cprvt_o to
11 il~=
n6fio-j of 4~ -The author con-.~,,Ars flalys
~about Wab OUr I fkt~p&te ~NingS With Due 0 NO sub
"dt' ruc r, Int ge
sonic leadii g edges, h q 5ubso i t aili I and
either sub- DT Supei-sonic leading edc; and at Jt sets of
callied fins cpuaposed pi pair. 0 -,3uch plates I hi -ed atiti-
synImetrica fly- Uith iespect On X-M(w s t,,nients
p" th 0 -Mac) ~Pn~' XIS NY ' CM. the-bDundary et n-qi'j)~J_ or
f
Diving* 1: ap~PIM61
.1; is-con t es
Stan , Fbr At 51 ti knip.
discussed j", 1= I and M, cone can b" mapp-15;d 0 1 A 1e reJ-
and imagin iry axes of a nL%v co-npli:x plan,- by e tarY
By'interpitking 11, '1;~ Lk StIvil fl"t I kill
(21 an flow, constant on cerij Is ht
- anto acr TI,. ~,if
segniews, and-by taking --ount tbc ii
gngulv~itit s "Wred at leadillgedgr-3. etc.,
,able to fine explicitly in tenns of 0einimtati In
-r!-.,smg N%)Ftex and douLL'.4 i! t A
by sup
j
A.
f -

I lie,
D' P(Wanct, el j)c 1,
IT
rms,
ovix

-7 ~7.
the front surface can be obtained fr,sm th(t thick-nesg
distribution as in the prmding paW.r. Ile author cort.
if~-turtts that nv~-' the reaT surfaces. to the accurm v A
(i--r as,!I?,

&ratlo 4t! 61 --lbifluerict des
,it e, '91 mr1w zfttdce.
S Lr F ulment rupemniqu autour
- wess.LMng-uwLb ft con;-ques, a ipaiss%mT et incidence
lsvaria~de& Com. k~ad. R. P. Romine 4,271-263 ~ 1 -45-4)

CA W OLI, E. ; ORVEANU, T.
CARAFOLI, E. ; ORVEANU, T. 14ecanicaifluidelor (Fluid
Mechanics): a book review P. 31
Vol. 1, no. 11 NoV.1955
ARIPILE PATRIEI
TECHNOLOGI
Bucuresti, Rumania
So- Eastern European Accession Vol. 5 No. 4 April 1956

CAWIIII DUkqTRESCU
Biconic narrow delta wings with variable incidence in
supersonic
currents. p. 237. Academia Republicii Populare
Romine. Institutul de
Ylecanica. Aplicata. STUDII SI CLT.CETARI DE MECANICA
APLICATA. Bucuresti.
Vol. 6. no. 3/4, July/Dec. 1955.
So. East European Accessions List Vol. 5i No. 9
September, 1956

CARAFOLI, E.
Scientific research for improvement of the material
base in the field of
machine construction.
P. 93
SUPP1. to v. 3, 1955
ANAISEIS
Bucuresti
SO: II onthly List of East European Accessions (EEAL),
IL, Vol. 5, no. 12
December 1956

J-711

f

we ing

pp.

936),

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noZZIes (11); 7.
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$04y, 2ponwing al (Wit Spuis
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HomogeneouB Bup)rsonle Flow Around.an Angular Wing
I/ Cgrafoli, Elie Vicoulement
I and Horovitz. Blatrice.
supersoniqu* honiogtne, d'ordre suptrieur, autour d'une
&He anrulalre A plaque normale. Acad. R. P. Romlne..
14%
-974. (Romanian.
Stud. rc. Mec. Apl. 8 (1957), 959
Russian anti French summaries).
Consider a body composed approximately of two.:
sectors of the xlx2 and X11.3 planes, with common vertices!.
at the origiii. To find the linearized supersonic flow about'
it parallel to the xraxis with velocity djs~ufio
on wing and plate of a type described below, the authorle,
seeks a velocity potential. O(xi, xa, xa) that is homogene-
OM151. of order n in zi,
X3, X31 By Euler's formula the velocity'
o Poneals u=Ojoo, v--lboia, w-Oooi are expressible!
m
c
as Imear cambination Of 0jqr-"/DXiV8X&f8Xsr, P+:
nctionn
q+r=n, with coefficients Mt are known fu
of 22. Y~--XEIXI. and x=x2,1xj. On the wing, approximately:
the ~~-Ix3 plane, for example, -I)Itvjxi%-I=-:
in (n
where C,1-10 is a binonual.coef-'

f
0 L -j
A)l It'
~T~ 71;; 1 V
W), J
-Vw I
ME
and [Daescu M. - Germtol theory of
3M. Ccarnfo
5T Rgivan p tsu;a Jjstrltll:~ (in French), Acad.'Rrpjwb.'
Pop. Rprtive. Rev. Macam AppL 3, 2, 5-21, 19M
Authots discuss the so-called reverse problem which consists
In detern-jaing the surface form (the warp) of a triangular wing in
imal"D LQX~M! the pressure' coefficient distribution being given
:under thu hirm of it highem,rder homogeneous polynomial,' The -
~cases *Ilc:h deftne the prollem, are then presented, pointing out
that eacl. ott thes e cases may be reduced to a direct eqUvalent
It follows that th reverse problem may he treated in the
in
proble
:same wnj at the direct problem, nemely through the ~ydtcdynAmiq
analogy previously proposed by Cuafoli. Ifowevet, in addition to
K the singtIpAtlex used to solve the direct problem, a logatithatic
sinSularl ty must be introduced at the ozlSio. It Is in this way that
11'j
;the soicit lori Is obta;oed. General solutions Rm given for the
tUck'
wing wlt1ijjbjjjWzjeadInS edges, lot the thick wins with one j
.. .... superson lc le*Jlnx edge, ad for the thin wing.
Practi,W applicadoz.8 bu:lude conical zootioct& of the first and
second a rat". T. Orovtsos, Ro
W
L :!g
~J

Carafoli, E. ; Horovitz, B.
Cruciform wings; mixed probloms of triangular wings fitted
with perpendicular
plate in suporsonic flow. p. 819.
Academia Republicii Populare Romine. STLMII SI CERCETARI
DE ~ECANICA APLICATA.
Bucuresti, Rumania. Vol. 9, no. 4, 1958.
Monthly List of East European Accessions (EEAL) W Vol. 9,
No. 2, January 1960.
Uncl.

Garafoli, E. ; Nastasej, A.
Study of thin triangular wings with forced symmstry in
supersonic flow. p. 833.
Academia Republicii Populare Homins. STUDII SI CERGETARI
DE 14ECANICA APLICATA.
Bucuresti, Rumania. Vol. 9v no. 4t 1958.
Monthly List of East European Accessions (EEAL) LC Vol.
9, No. 2, January 1960.
'Uncl.

9040
RUM/8-59-1-1/24
AUTHORS. Carafoli, E.. Sgindulescu, S.
TITLE: Aerodynamical Characteristics of Ailerons Having a
Harmonic Oscillation
in Supersonic Region \
PERIODICAL: Studii qi Cercetiri de Mecanic6 Apliaat~, 1959, Nr
1, PP 7 - 4o (Rum)
ABSTRACT: This is a study on harmonically oscillating motions of
ailerons atround
a joint. The authors establish in a preliminary section all
important
data, as follows: Considering a system of ocordinates Ox x2x ,
the
- "'Zc1,,. U~-
hypothesis of small disturbances is given in Equation 1, In -
is the speed of the nondisturbed flow directed after the Ox,
axis, a,
the speed of the sound, Me,. the respective Mach n1mber and V
(Y: llx-,,'x3, t)
the motion potential. Notating the pulsation of a pe.-Iodic
motion with W
the authors introduce the Equation 2; "h" being a reference
length, 'e.g.
the wing chord. In case of a harmonic oscillation mo-tion, the
motion
potential could be [Ref 1] expressed in Equation 3, in whi3h the
reduced
potential 0 (X is independent from the time, and its der-1vation
in ratio of x3 s e vertical reduced speed", according to
Equation 4.
Computing the partial derivations of the motion potential and
suLstituting
Card 1/ 10 them in Equation 1, the reduced potential are given
In Equation- -9. L,

&)410
RUW8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
Considering a polygonally shaped aileron which has an oscillating
motion
of small frequency around the joint 00, the oscillating motion cf
the
OA'A'Ox surface can be obtained by superposing the following
harmonic
1 4.
oscillating motion lRef 21 e-L G-" of the 0A'A' surface around
1 2
the OA21 axis, and S I eitj t o? the 6A I q surface around the
ON1 imaginary axis (hgure 1)o Decomposing 7Ae first oscillatilig
motion
into its components and using the previously established general
formulas
[Ref 2], the authors deduce for the elevation of the point P of
1:1he co-
ordinates xl,x.,,, (Equation 7) respectively for the vertiEal
reduced speeds:
~2x, i + (Nr 8'). Pro-
0 = -E2, (Nr 8) and i ElX2
sc,z
oesding in a similar way In case of the second o L1 ating motion,
the
elevation of the point PX of the coordinates x1, x2P is axpressed
in-
Equation 9, and the reduced vertical speed by.- fro = %, (Nr 10),
r
i -j- [Elx2* - E 1 + (Nr 10'). Based on the foraralat~ 8
2x1'
the reduced poteniials of both oscillating motions are expressed
by:
10; - ~ 3 + I -A -(~ , ~?' . (~*l + I h 1* , (Nr 11). The
expressions
of the pressure '&f Heients C and "' c'an bl-oo~tained fr*om the
pressure
C~
equation of a nonpermanent moi~on given In Equations 12 and 121.
The
Card 2/10 reduced axial speeds:

80410
Rum/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic-
Regions D Val
U0 Ia U0 5 *'- (Nr 13)
can easily be determined by using the results of previous
works,[Refs 4
and 5]. Using on the other hand the formulae of Baler for the
potentials
~ 1 and 1+9 , the authors obtain: ~ 1 = xj(uo + yv ), and 0* XI*
(lift 'r tNr 14), and considering the cornection '10)etween
thelr;spective
0 + yvl*)
ID
reduced speeds, deduced from the compatibility relation, the
potentials
01 and (Vl can be easily determined, if UO respectively u" are
Imowm.
The authors then are examining polygonally shaped aileronsowith
subsonic
and supersonic leading edges, triangular ailerons, trapezoidal
ailerons,
trapezoidal ailerons with subsonic and supersonic edges and
rect&A-igular
ailerons. At the study of harmonic oscillations of ailerons with
subsonic,
or supersonic leading edges, the joint can have every position
irL ratio of
the Mach cone. The expressions of the reduced axial speeds and
of the
potentials of both oscillating motions have been determined in a
previous
work [Ref 2] and are not derived any more, but only mentioned,
since they
define the pressure coefficients G and C*. In case of an
oscillatLng
p
motion of the OAjAp' surface (Figure 2), iRe aileron has a
supersonic and
Card 3/10 a subsonic leading edge (OA'), as well as an OAL edge,
which makes the 1-j

80410 RUM/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
reduced vertical speed to have a leap of 0 value to left and of
P3 value
to right for the homogeneous of the first order and from 0 to P 1
?or the
homogeneous motion of the second or-der. In these conditions the
authors
establish the expressions u (Equation 16) and 4), (Equation 16")
for the
homogeneous motion of the f?rst order, and u1 (Equation 17) for
tshe homo-
geneous motion of the second order. Studying the oscillating
motion of
the dAJA' surface the authors consider an aileron with supersonic
leading
edges, t9e reduce'do vertical speed being zero, and ~ 0 being in
its interior.
The homogeneous motion of the first order is given by u0ft
(Equation 18)
and ~' (Equation 181). In case of the homogeneous motion of the
second
order, the red-aced axial speed can be obtained by the expression
U'
(Equation 19). The authors then compute the lift coefficient, G
zl1 being
the partial lift coefficient as an effect of, the first
oscillating motion
and Cz, resulting of the second. oscillating motion. If the joint
OVI is
subsonic, -the lift coefficientE can be computed according to
Equations 23
and 231. For the computation of the proper lift coeffi-,,ient of
the proper
aileron .9 the authors deduce the: expressions, 25 and 251. in
case of a
supersonic OOK joint, the partial lift coefficients are more
simple than
Card 4/1o in the Equations 27 and 271. At the calculation of the
resistance co-

F% j" 10 RUM/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
efficient, the contribution of the total power produced on the
alleron,
,contribution of the power which acts only upon the mobile 0AIAPY,
surface,
and contribution of the suction which appears only in case of
subsonic
leading edges have to be taken in consideration. The resistance
coefficient
el
C at the advancing is given irt Equation 29-:- 8 being the area of
the
Xf m It if
OAlAjO* mobile surface. The axial disturbance speed u , given in
Equation
33 is deduced from the Equation 3. Replacing l" and by the
expressions 16, 161 and 17), making x --o.1 anT putttinxg into
eVlence the
factor ~r_r, the expression for (u), - 1 INr 34) is deduced. The
suction,
force So can now be calculated by a simp e integration. The authors
finally deduce the expression for C (Nr 35) which is the same for
every
position of the joint against the Ax9h cone. This term becomes
imaginary
if the OA11 leading edge baoomes supersonic. Notating with C the co-
efficient of tile rolling moment of the first oscillating motion
imd with
V the coefficient of the rolling moment of the second oscillatil)g
motion,
ike total coefficient of the rolling moment can be expressed by
Equation
36. If the joint 00y' is subsonic, the coefficients of the rollirg
moment
are given by the expressions 37 and 37'. In case that the joint OW1
is
Card 5/ 10 supersonic, these coefficients are given by the
expressions 39 w,-.d 39'.

RUM/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
The coefficient of the pitching moment is given by:
C M C *~ 0~ :,_ (I _ h C (Nr 40),
ma ml M h z
in which the coefficients of the pitching moment appearing as an
effect of
the two motions CM1 and CM111 are given by the relations 41 and
411. if the
joint is subsonic, the coefficients of the pitching moment are
given by
the expressions 42 and 421. The coefficients referring to the
proper
aileron, are given by the relations 43 and 431. If the joint is
Super-
sonic, the coefficients of the pitching moment are-supplied by the
Equations
44 and 441. 7he coefficient of -the control surface moment cmea
can be ob-
tained from: Cmca - Cmal + qG1 (45) in which Cmcl results from the
first
motion and CQ from the second oscillating motion. The partial aero-
dynamical coefficients which interfere in the formulae 46 and 46'
refer
only to the mobile surfaces. The authors then proceed to the
calculation
of the coefficients of polygonal ailerons with a supersonic
leading edge.
The OA21 edge of the OA'A' surface (Pigure 4) causes to the
reduced vertical
1 2
speed a leap of 0 value to left and of P 0 value to right, for the
homogeneous
motion of the first order, respeotively from 0 to ~ 1 for the
homogeneous
Card 6110 motion of the second order. In -this situation the
authors have already

8041c)
Rum/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
established in a previous work [Ref 2] the expressions for the
reduced
axial speeds and reduced potentials: uo, ~ 1 (47 and 47) for the
homo-
geneous motion of the first order and u (Nr 48) for the homogeneous
motion of the second order. Regarding the oscillating motion of the
O*A~A' surface, the reduced axial speeds u". and u * respectively
the
s
poten are defined IV the relationo (18, 16 ;n~ 181). in this
situation the pressure coefficient C`~'(Equation 121) remains
unchanged,
a fact which causes that the partial Paerodynamical coefficient
remains
also unchanged. The lift coefficient of the subsonic leading edge
can be
computed by the relation 20. The lift coefficient referring to the
whole
surface covered by the Mach cone, the 00*-Joint being subsonic, can
be
computed in relation 49. If the 000 joint is supersonic, C zi is
supplied
by the relation 51. Resistance coefficient at the advancing: il' the
leading edge of the aileron is supersonic, there is no suction
force, thus
the formula 29'i simplified in Formula 52. If the 00" joint is
subsonic,
I t~3
C will be replaced by the expression computed for the entire
surface
aftected by the oscillating motion of the aileron. q and C ZI wi,11
be
Card 7/ 10 replaced by the relation 251, respectively 50. S and-ISM
~~re the surfaces

904D,
RUM/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
OAIDI respectively OA'AA011 (Figure 4). If the joint is
supersonic, U.,
islZge' lift coefficiQ of the aileron and Cz:L and Ct are given'by
the
formulae 51 and 271. The total coefficient of the rolling moment in
ratio of the Oxi axis is given by the formula 36. If the 00"'
Joint is
subsonic, the coefficient of the rolling moment is given in
relation 53.
The same coefficient of the proper aileron is given by the
relation 54
and in case the joint is supersonic by relation 55, C* being given
by
Nr 391. The coefficients of the pitching moment are given in case
the
joint OOA is subsonic by the expression 56; in case of the prope;
aileron
by the expression 57 and in case that the joint is supersonic by
the ex-
pression 58. The formulae which allow the computation of the
control
surface moment were previously mentioned in Ecluations 45, 46 and
461. The
results obtained above can be also used for the computation of
triangular
ailerons. In case of trapezoidal ailerons with a subsonic leading
edge,
the expressions of the reduced-axial speeds and reduced potentiala
can be
deduced from the relations of the polygonal ailerons. The partial
co-
efficients of the first oscillating motion are given by
expressions 60,
card 8AO 61, 62 and 63, and for the second oscillating motion in
expressions 64,

RUK/8-59-1-1/24
Aerodynamical Characteristics of Ailerons Having a Harmonic
Oscillation in Supersonic
Regions
the partial coefficients referring to the entire surface
affected by the
oscillating motion of the aileron. Finally the authors present a
table
of constants.
There ares 5 diagrams and 5 references, 2 of which are English,
2 French
and 1 Rumanian.
SUEMITM: October 28, 1958
Card 10/10 V~

CARAFOLI 3 E. ; 11AT P-E.IJIC U, D.
Supersonic flow around the system carrying a conic
winc fuselage. In
French. D.377-
RT111E DE MECANIQLE APPLIQU-1- (Academia Republicii
Populare Romine.
Institutul de Mecanica Aplicata)
Buciiresti, Rumania
Vol. 4, no. 3, 1959.
Monthly 1-ist of E-stern European Accession Index
(EDI) TL vol. 6, Nlo.
November 1959
Uncl.

R/008/60/000/001/001/oog..
0. fo 12. ID A125/AO26
AUTHORS: Carafoli, Elie and Mateescu, Dan
I
TITLE: General Method of Determining the Interference of Wing
and Conical
Fuselage in Supersonic Regime
PERIODICAL. Studii 91 Cercetdri de Mecanica Aplicatd, 1960, No.
1, pp. 11-4'r
TEXT: In a previous work (Ref. 1), the authors presented a
method of
solving the problem of supersonic flowlaround a wing/conical
fuselage system.
In subject article, this method is extended to.the case of a
wing with edges
on which there are incidence and inclination leaps, thus
establishing a general
method of solution of the supersonic flow around the
wing/conical fuselage
system. Considered is a wing/fuselage system (Fig. 1), where
the fuselage axis
has the incidence - 0 against the undisturbed flow U. , and the
wing hiLa a
constant incidence and inclination. The authors assume that the
fuselage has
reduced dimensions against the Mach cone (B202 -:~~ 1), that
the incidence and
the inclination, as well as the M 0 incidence of the fuselage
are small enough
for the application of the theory of small disturbances. The
stream around this
system can be decomposed into: I) symmetric axial stream around
the isolated
Card 1/4

R/008/60/000/001/001/009
A125/AO26
General Method of Determining the Interference of Wing and Conical
Fuselage in
Supersonic Regime
conical fuselage without incidence; II) motion around the conical
fuselage/thin
wing system; and III) motion around the conical fuselage/symmetric
thick wing
system. The authors treat the last two motions and first present
the usual
notations and formulae. For the solution of the problem they
deduce the boun-
dary conditions of the function U . Based on the function (13) and
the compa-
tibility relation, the solution of the motion is expressed by
(14). The boun-
dary conditionslare now more-simple and can be expressed by (15),
(16), (17)
and (18). Based on the conform transformation (3), the relation
(19) is cb-
tained for the X plane, from which result the boundary conditions
(20). (21),
(22) and (23) in the X-plane (Figs. 3a, b, c). The function 4) a
presents the
same singularities (24~, (25) wS (26), and satisfies the boadary
condition
(23) as the function thus: - = "U a, (29). Replacing - by its
value from
_ff~ dX
(19) in the relation ), the axial disturbance speed u, ~hffi is a
real part
of the expression (30) is obtained. rU a and C a of this
expression represent
the solution of the conical stream around the fictive wing. Thus,
the problem
of the supersonic stream around the win&/conical fuselage system
has been re-
vAra PA

R/008/60/000/ool/ooi/009
A125/AO26
General Method of Determining the Interference of Wing and
Conical Fuselage in
Supersonic Regime
duced to a conical stream around a fictive, isolated wing with
variable incidence.
In paragraph 3, the authors determine the solution of the
problem for differ-
ent particular cases selected in such a way that, adding the
effects, the so-
lution of the general case of the wing/conical fuselage system
could easily be
determined if the wing incidence is constant on the sections.
They first treat
the case, where the whole system has the same incidence and
then some cases
where the wing has incidences oD the sections which are
different from that of
the wing. The following particular cases are examined: 1) The
wing and the
fuselage have the same M 0 incidence; 2) The wing has an MO
incidence on the
M A, section, the rest of the wing and the fuselage axis
having no incidence;
31 The wing has an incidence OC2 on the A M2 section, the rest
of the wing and
the fuselage axis having no incidences; i) The wing has an M
incidence on the
A2M2 and AlMl sections, the rest of the wing and the fuselage
axis having no
incidence; 5) The whole wing has an M incidence, the fuselage
axis having no
incidence; and 6) Application examples, where the authors
present the expres-
sions of the axial-disturbance speeds for the most interesting
cases., Finally
card 3/4

R/008/60/000/001/001,1009
A125/AO26
General Method of Determining the Interference of Wing and
Conical Fuselage in
Supersonic Regime /C/
they treat the motion around a conical fuselage/symmetric thick
wing system
(Fig. 4). There are 3 figures and 3 references- I Rumanian, I
English and
I Austrian (German).
SUBMITTED: October 29, 1959
Card 4/4

8h648
4
R/008/60/000/002/001/007
10 ON A125/AO26
AUTHORS: Carafoli, Elie, and Mateencu, Dan
TITLE: -19iip~erson~ioFlow' Around a Conical Cross-Wing~ ~seiag
System
PERIODICAL. Studii si Cereet9ri de Mecaniog Aplicatg, 1960, No.
2, pp. 325-337
TEXT- The authors treat the problem of flow around a conical
cross-wing -
fuselage system1provided with a normal plate (Fig. 1), for the
case where the
leading edges of the wing and of the plate are subsonic and the
angle of imidence
of the fuselage differs from those of wing and normal plate. The
study starts
from the hypothesis of minor disturbances, taking into account
that the dimensions
of the fuselage are small enough in relation to the Mach cone,
and that the angles
of incidence of wing, normal plate and fuselage are also
sufficiently small. The
general flow around the system investigated is decomposed into
three movements-
the Ist is the axial-symmetric flow around the bare conical
fuselage - which is
known -, the 2nd is the flow around the system symmetric
plate/fuselage - which
was the object of another paper by the same authors (Ref. 1), and
the last one
is the flow around the system cross-wings/fuselage, with the
plate and the fuse-
lage being without lateral angles of incidence; this latter
movement is the sub-
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84648
R/ooB/60/000/002/001/007
A125/AO26
Supersonic Flow Around a Conical Cross-Wing/Vuselage System
ject of this paper. The problem Is referred to a conveniently
chosen plane
where it is reduced to the problem of determining two simple
movements: a coni-/
ca" one around a very thin cross-wing, and a plane one around a
circle. The au-
thors give the general expression for the axial speed of
disturbance LL, indi-
cating the method of determining the constants. There are 3
figures and 4 Ru-
manian references; 2 of these were published in English and 2
in French.
SUBMITTED: February 12, 1960
Card 2/2

AUTHORSi
TITLE-
PERIODICAL-
R/008/60/000/003/001/007
A125/A026
Carafoli, E., and Sa"ndulesou,
Harmonic Oscillating Motionof Tails at Supersonic Speedi
Studii 91 CercetAri do Mecanich Aplicat9, 1960, No. 3, pp. 557-568
TEXT: Subject article analyses some problems regarding the
non-perjr-.anent
eupersonio flow around a tail referred to an orthogonal system of
coordinates
OXIX03. Supposing that the points of the horizontal and vertical
surfaces have
a harrho-nic motion (Ref. 2, 3),the components of the normal speed
on the horizon-
tal and vertical surfaces are defined and the components of the
reduced normal
speed are determined by the expressions (6a) and (6b). The
pressure coefficient
shows that for the determination of the pressure on the tail it is
necessary to
know the reduced axial speeds and the reduced potentials. This way
a seriffs of
problems regarding the harmonic flow around the tail can be
solved. The authors
examine two cases: a tail moving in a disturbed and harmonically
non-stationary
flow behind the wings (due to the vibrations of the wing); and
oscillations of
the tail around the center of gravity of the aircraft. They first
consider an
oscillation of the tail of small frequency and amplitude around an
axis, having
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85031
Harmonic Oscillating Motion of Tails at Supersonic Speed
R/008/60/000/003/0()1/007
A125/AO26
any position in the space. In this casethe reduced vertical
speed on the two
surfaces can be determined. The problem is finally brought to
the study of the
conical motions of the first order defined by the potentials(~
1 and (P'4, and
of a conical motion of the second order defined by 4)2- The
reduced speeds cor-
respond to the harmonic oscillating motions of an isolated
wing, identical in
shape with the vertical surface. The conical motions
corresponding to the re-
duced speeds are studied considering the interference. The
pressure coefficient
of this motion is expressed by the relation (17), which can be
expressed by know-
ing the expressions (18), in which uo and 4 are the reduced
axial speeds of the
conical motion of the first order and u1 the reduced axial
speed of the conical
motion of the second order. Using the general results
previously published in
(Refs. 6,7) u0 Is determined by, the expression (25) and ux by
(30). Starting
0
with the formula of Euler (31) the authors deduce the reduced
potentials of the
conical motion on the horizontal (1~10r) and vertical ( 4) jv)
surfaces, express-
ed by. (35a) and (35b). Starting agaln w1th the formula of
Euler (37), they de.-
duce t~e reduced axial speeds of the conical motion of the
second order on the
horizontal (ulor) and vertical (u1,) surfaces,expressed by
(43a) and (43b), The
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85031
R/008/60/000/003/'001/007
A125/A026
Harmonic Oscillating Motion of Tails at Supersonic Speed
authors finally determine the constants used in these
expressions. There are
2 figures and 9 references- 6 Rumanian (4 published in French,
1 in English
and 1 in Rumanian), 2 English and I Soviet.
SUBMITTED: March 9, 1960
Card 3/3

0. 9W
AUTHORSt Carafoli, Elie, and Ngstase, Adriana
23654
R/008/60/000/004/001/013
A125/Ai26
TIM: Thin triangular wing of minimum drag In supersonic stream
PERIODICAL: Studii gi CeroetKri de Meoanioa Aplia4g, no. 4,
196o, 817 - 833
TEXT: The authors determine the shapm of-a thin non-symmetrioal
trian-
gular wing, having a minimum drag, when lift, diving moment
andplane projection
are given. 4 treating the non-symmetrical triangular-'wing,
they are considering
the general case which is then applied to delta wings,
polygonal wings and tra-
pezoidal wings, az performed in a previous paper (Ref. I.- Elie
Carafoli, Adriana
Nastfise, Aripi trapezoidale de rezistenJA minim& tn ourent
supersonic. (Triangu-
lar Wing of Minimum drag in Supersonic Stream) Comunicare
flawra la Primul Clon.
gres Unional. de Mecanial teoretica" 91 aplioatlt de la
Moscova, Ianuarie 27 - Fe-
bruarie 3, 1960 [sup tipar, In revista sovietiol Mekhanika]).
Furthermore, the
authors assume that there is an additional separation edge OC
on the wing (Figure
1), which can eventually be taken as the joint of a
leading-edge flap. Suction
forces appearing on the subsonic leading edges have been
included in the calaula-
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23654
Thin triangular wing of minimum drag ....
R/008/60/000/004/001/018
A125/A126
tion of the drag. Considering the general expression of the axial
disturbance
speed u given in a previous work by E. Carafoll, M. Ionescu (Ref.
13: Ecoulements
conique d1ordre supbrieur autour des ailes triangulaires minces ou
A 6paisseur
sym6trique. Revue de Mboanique Appliqu6e, 1, 1957), the authors
could systemize
the (jaloulation in such a manner that the determination of a
triangular wing
with separation edge and minimum drag in reduced to the calculation
of a single
type integral, which they designate I and for which they give a
formula-of
simple algebraic recurrence. The auIrs then indicate the
application afthe fiL4
to all wings with minimum drag being used at present: delta wings,
trapezoidal
and rectangular wings, and polygonal wings. There are 3 figures and
14 references
5 Soviet-bloo and 9 non-Soviet-bloo. The four references to the
R*Iish language
publications read as follows: E. W. Graham* The Calculation of
Mifiimum Supersonic
Drag by Solution of an Equivalent, Two-dimenhonal Potential
Problem. Douglas
Aircraft Report, SM-22666, Dec. (19-%); - Note on the Use of
Artificial Distri-
bution of Singularities in Supersonic Minimum Drag Problams,
Douglas Aircraft
Corporation, Report No. SM-23022, Dec. (1957); E. W. Gritham, A
Geometric Prob-
lem Related to the Optimum Distribution of Lift on Planar Wing in
Supersonic Flow.
Journal of Aero-Spaoe Siences, Dec. (1958); Kainer, Calculation of
the Optimum
Supersonic Delta Wings. CONVAIR (Sar. Diego) Report ZA 259 Oat
(1957).
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23654
R/008/60/000/004/001/,318
Thin triangular wing of minimum drag .... A125/Ai26
Figure 1: Non-symmetrIcal triangular wing.

EMIUMV-1- (Bukharest) LCarafoli. Elie]
Theory of simple and cruciform aelts, wings in a
supersonic
flow. Insh.sbor. 27:17-28 160o (KM 13t6)
(Airfoils) (Aerodynamics, Supersonic)

CARAFOLI, Elie, acad.
Development of scientific research in the Institute of
Applied
MIchanica of the Rumanian AcadezV. Studii core mee apl 11
no.6:
1345-1360 '60.
1. Membru al Comitetului do redactie ei redRetor
responsabil,
"Studii 9i corcetari de mecanica aplicata.11

10.12(o
"' P 3 96
R/008/62/013/002/001/009
D272/D308
AUTHORS; Carafolij Elief and Mateescu, Dan
TITLE: Interference between wing and body in high order
conical flow
P13RIODICAL: Studii si cercetdri de mecanicd applicatd, no. 2,
1962, 275 - 294
TEXT: As a continuation of previous studies on the conical
superso-
nic flow around simple or cross-shaped wings with conical body
(.Re-
vue de M6canique Appliqu6e, Acad. R.P.R.f no. 3, 1959, no. 2,
19609
no. 3, 1960, no. 3, 1961) the system wing-conical body, placed
into
a supersonic current, is studied in the case when the wing
incidence
is distributed in the wing plane according to a function, which
can
be represented as a sum of homogeneous polynoms of different
orders.
This case is considered under general conditions, when the
vertical
velocity distribution on the ving is different on its various
por-
tions separated by vector radii drawn from the tip. It is
assumed
that the wing is fitted with ridges which separate two
different re--
gimes of incidence distribution. The method developed permits
easy
Card 1/2

Interference between wing and body ...
0
R/008/62/013/002/001/009
D272/D308
solution of the problem in the case of nonuniform flow, as well
as
of the Droblem of low frequency oscillations of the same system,
which in fact reduces to the study of two conical motions of
diffe-
rent order. The case of the thin wing is treated first,
considering
for this purpose a conical motion of n-th order around the
system,
the axis of the body being parallel to the undisturbea flow
velocity
and the wing incidence, and hence the vertical velocity on the
wing
being distributed in the form of homogeneous polynoms of
(n-l)th or-
der. It is then proved that the problem of the supersonic flow
araxnd
the system considered, can be reduced to determination of a
ce3'tain
function corresponding to the flow around a fictitious wing only
with a certain incidence distribution. This function and its
con-
stant parameters are determined. The method is then extended to
the
case of the 'system body-thick wingg and to the system
wing-conical
body placed into a non-uniform flowp determining in each case
the
function and its constants. There are 4 figures.
SUMUTTED: December 27, 1961
Card 2/2

349ja
21/0 03/6 2 / '000/001/001/007
3-272/D304
A'oTH-OH3 ~~~~and Ghia-Nastase, A-riana
"i -1 ic-:~-
T 15- L-' - -nipmalm dra- problen of the winr of
SymrAot"-icai t Li
ness 1-t Supez.-Sor-ic flow
3
IC'L: '--ecanicA a -2, 11-24
plicatAkno. 1, 190
T ---'X, 12 T'-,--,e ouri)ose of tl-le study was to
deteraline the s-'-ape 0: -Lne
0 ini-lum di rag
surface of a win- with Symme' Gric thickness, havip-,f,,-,
rai t3
in suoersonic currents. It is assumed that several Seomctricrd
corldliuions are given -- the plane projection (an
asy-1::ietrica--
an-de), the volune of' the wing, P the w4ncr on J-~s
-D the closing o- - 0 -
leadin- a-ad trailing edges, thle continuity of the iv'ing
surface a-b
C:)
61--e crossing o-f --,)- ed:-e; for ---,eneraliZation, it
J--- also ass,,Lmed
-'D
Wlat the wing is fitted with a separation rld~e. The
vE.-ri-at-Jonal
C~ U
me-t,hod was chosen for the present study, but -for the axial
per-
Uurbat-Jon velocity u the aut-hors used an e-x-pression
derived '--,y E.
Carafoli and 111. Ionescu (lle----. 11i : '-Revue de
1116ca-nique "Lp-Lique'e,
no. 1, 1957). The uroblem is reduced to a sinzle Uype of
intuel-ral
Card 112

R/003/
7 ')~2/000/JO1/JO1/CjO7
-Droolem of th--:~ winr-, I ':
Ei-zimum. drag D2 2 304
which is denoted by I., a.---d for whicl-I a simple Elgebraic
recurre-n-ce
0
formula is -iven. The results are discussed, indicatinLt;'-
tuIiat they
can be particularized viith- case, obtaining several %Prings of
P:f-ac-
tical importance -- t1le delta wing, th.e trapezoidal win-, t1re
rectangular wing, and the poly-onal wilng. These winas a--e then
analyzed in tuh-- two possible cases for each vrith or wi th.ou7,
ed,,-es -- by means of the relations obtained the 1-ge-neral
ca-t3e.
It is. concluded thc-tt tbesc results will enc-;.ble the
~;t'.,dy of vrincs
-;~ '--enerai shaDe with nmi'nimum drag as well as of thick ;.-i
s
0
11 U~ n'-
vided with- norl~-,al olates ai,d ~jj-e 21
Coures and 14 rel'orences: 8 Soviet-bloc and b non-Sovi-ut-bloc.
r-;'.,.e
4 most, recent references to the Bnrr~"ish-lan-uiL-e ub 1 4-1 c
a t i :) n s
~> 13
read as follows: W. .7. ulraham - Douglas --Ii~-craft
Corz)3i-a-v--'I Dn
po:---ts, S. 11-1. 2206606, Dec. 1956, S. 1% 23022; 1.!. 1.
Gra-'---am a.,,d I-Pa .
Lac--erstrom, D. A. C. R. , S. .11. 23901, !larch 1~160; P.
S'trand
nimu-m %linr, V.'ave Dra- with Volaime Constraint. journal ol'
A-ro
Space "Icience, ALI,-USt (1960).
SU31;T"TED: October 11, 19051
Card 2/2

CARAFOLI, Elie, sead.
S=e theoretical considerations on lateral fluid
Jets. Studii
core mee apl .13 no.5.S.1061-1072 162.
1. Heikbru al Comitetului do redactio pi redactor
responsabilo
"Studii si cereetari de uscanick aplicital.

. CARMLI # K.; EZRHMM, C.
Aerodynesic characteristics 6f profiles in
supersonic-
hypex-sohic flow in the 6aso of neglecti~ig the
pressure
losses due to shook waves. Fav mec appl 8
no-5t729-744 163'o

-.CAMFOL-I, E.; BEREENTE, C.
Aorodynamic characteristics of profiles in supersonic-
hypermonic flow in the case of neglecting pressure
losses
due to shock wavea. Studii cere meo apl 14
no.4,751-.767 163.

I'AP,404r')'W,~

7
Carat
AUTI OR:

-'~;TITLE De terin

~to shock-.wav-ed

'SOURCE R

-
---.'.'TOPI.C-
-.TAGS-:-- :A

-,proil-le ~.presis~

...ABSTRACTi b

h
ndetermining.

-app quee ca

nalytical exp

.--dynamic prof i V
waves area.

-,Cord.-
SD FVII
I C~,E r
b
hat'i-ow-7; f-`,th;q

zl; ~.72L' 7-j!
-:El hi -;Z, 'If
MOO- TPd "/J5-;s-A/h%h 3

-d-Vdt-- -I'--
c6afficients rn-aAAo,b-6-Mv- efifi6 hout GiW ptegration. The r
Is usti-here for the c mination- (t4tiAn a supers
bter
zoidhl wing having the minimum drag, as. well aB t
.-Plong projection (assuniW1 a symmetrical trapezol
VIM,
:.00
J., Olt do
it SOV.-
do flow) of the surface of a thin
lift, pitob, isentral proftle, and the
prig. has: 65 forraulas and

A k "M
-L 1-5723 A( T72/' FCS )~IrDw
ikA01.) 31-1
ACC NR. ArimO145 SOURCE CODE: RTJ/0008/65/019/004/0991/1007
Radulescu, S.
AUTHOR- CaT!L-
ORG: "Tralan WWI Institute of 11uid Mechanics,, Academy of Rumanian
R. S. (ii&titattd
de mecamica fluldelor 'q'r--aTa-n-Wa" al A-c-ademlei R. S. Romania)
TITLE: The supersonic flow around a, thin delta wing In drift
SOURCE- Studii st cercetarl de mecanica aplicata, v. 19', no. 4,
1965, 991-1007
TOPIC TAGS: aerodynamics, supersonic flow, thin wing, delta wing
ABSTRACT: The action of the drift on the ite ic c~'
jodynam aracteristics of a thin delta 3KIM
is Investigated In the case of supeTsonic conical flows. By applying
the residues method,
the aerodynamic coefficients for a wing in which both edges wre
subsonic, are calculated.
For a wing with a subsonJe and a supersonic edge, only the rall and
turn coeff icientis are
given, because the smallvalues of the dL
Aft have Ft negligible effect on the coefficients of
attitude# resistancet and drag, Orig. art. has: 104 fannulan.
0
SUB CODE: 2d SUBM DATE: 28Apr65 ORIG REF.- 002
Card -1

ACC NR, ~P 6 Y7106 2 7
50253~3 SOURCk CdDE:
AUTHORs Carafolis E.,
ORG: Institute of'Flui.d.Machanice of the Academy of the R,P.R,.,
Bucharesf-_
TITLEt Extension of conicAl motions to quasi-conical motions
SOURCEt Revue Roumaine des sciences technique. Serie de mecanique
applique,, v. 109 no. 39 1965, 627-635
TOPIC TAGS: motion mechanics, conic flow, swept wing, pressure effect,
pressure measurement, surface pressure, aerodynamic characteristic
ABSTRACT: Problems of conical and quasi-conical motions as applied to
modern types.of aircraft were analyzed. The author extends the conical
and high-order conical flows to the so-called $1pasi-conical flows, to,
essure on the)
calculate the EE_- , surface of .1jing i-dr on the wing-body sys-
tem.Ainploy-ed In aeronautics. For simplificativng only methods and in-
dic9tions were given witho lot developing all the applications in the
1 .1
case of,high-order conical r quasi-conical motions. A more detailed
analysis a-d- more general. applications swill be -gT-veh in
future-voikso
OrIge. Art*' hast 4 figures-and 40 formulas. [Based on author's abstracQ_
-SUB - OODE2. Olp 2J0/ suBm DATEt - i9reb65/ oTH Ru , om INT),
Card I/V f~K_*i

At-k- INK: JW:)V.L4W,~P Awl, bWAVE WDS:
KU/VL).LY/D:)/U.LU/UUL-/V40Y/UW4
AUMOR: Carafoli, E.; Mateeecu, D.
ORG: Institute of Applied Mechwics of the Aegd= =I gj~
-of Oe Bom an Peo
'Pub Lic 'Flnotitut de Mecanique App3ique de l'Academie* de la,
Republique Populaire
Roumaine)
TITLE: A class of Delta wingolbose incidence and-slope vary in
accordance with
homogeneous ftmetions under MMrsonic conditions
SOURCE: Revue Roumaine des sciences techniques.. Serle de mecanique
appliquee.4
ve 10, z~pa 2# 1963j 489-504
TOPIC TAGS- Delta-ving, perturbation, function, wing incidence
ABSTRACT: Higher-order conic motions.are applied to the study of
triangular wings
with variable incidence and slope (or corresponding vertical
velocities), ulling >(O
homogeneous functions of various orders. To this.end, the problem is
reduced to
a study of a wing having an unbroken interval of,basic stops which
makes it possible
to use the results obtained by the authors in their previous
studies. As practical
examples, the expression is determined for the axial velocity of
perturbation for a
series of thin wings of symmetrical thickness mhose incidence and
slope vary in ac-
cordance with homageneous,functione of the order of zero and one.
Orig. art. has:
6o formulas. [DWI
SUB CODE: Ol/ SUBM DATE; 0Tjan65/--Mar65 OTH REF.- 002/
'Card 1.11

L 34383-66- EWP(m)/EWP(w)/T-2/EWP(k) WW/EM
ACC NR, AP6022636 SOURCE CODE: RU/0019/66/011/003/058T/o613
AUTHORi Carafoli, E .1 Berbente, C.
I' ORG: [Cwafoll) Institute of Fluid Mechanics, Academy of the
Socialist Republic
of Rumania; [Berben-te-T-Porlytechnic Institute G.
Gheorghiu-Dej , Bucharest
TITLEt Determination of pressures and aerodynamic
characteristics of
delta wings in supersonic-moderate hypersonic flow
- 11A4 -I
SOURCE: Revue Roumaine des sciences techniques. Serie de
mecanique
appliquee, Y. 11, no. 3. 1966, 58T-613
TOPIC TAGS: hypersonic aerodynamics, aerodynamic characteristic,
aerodynamic drag, lift, wave drag, pressure distribution,three
dimen-
sional flow, delta wing, angle of attack
ABSTRACT: The formula for calculating the pressure distribution
on
aerodynamic profiles in hypersonic (M. = 7) flow previously
derived
by one of the authore is applied to the case of a
three-dimensional
flow regime, in which an equivalent deflection 0 is introduced
instead
of the deflection T of the flow, which can be expressed only in
terms
of the axial disturbance velocity which is denoted by u and is
deduced
by the small disturbances method. Consequently, the formula has
the
advantage of being a function of this velocity alone, whose
expression
Card 1 / 2

L 34383-66
ACC NRs AP602263
is perfectly determined from the conical flow theory for all
cases of
current application. The relative effect of the boundary
layer on
pressure distribution at various M in discussed. The conical
thick
wing, the delta wing with constant slope, the double conical
delta
wing, the rectangular wing with diamond-shape profile, and
the wing
with double parabolic profile were considered. Comparison of
the
results with available experimental data concerning both the
pressure
distribution and the overall aerodynamic characteristics
shove that
the formula may now be successfully employed in,,exact
calculations of
the aerodynamic characteristic of various profiles in the
wide range
of angle of attack (up to IT*) and Mach numbers considered
here. Orig.
art. hast 18 figures and 63 formulas. CAB]
SUB CODE: '20~ -SUBM DATE: 28Jdn66/ ORIG REFt 004/ OTH REFs
003
ATD PR9SGt_,~-,jS_j
Iv
2

ACC NR, AP6029839
AUTHOR: Carafoli, E.; Pantazopol, D.
SOURCE CODE: RU/0019/66/011/004/0379/0892
ORG: Institute of Fluid Mechanics, Academy of Sciences of the
Socialist Republic of
Rumania (Institut de Mecanique des Fluides, Academie de Is
Republique Socialiste de
Roumanie)
TITLE: Deviation of a two-dimensional supersonic flow by a
jet-flaD
SOURCE: Revue Romaine des sciences techniques. Serie de
mecanique appliquee, v. 11,
no. 4, 1966, 879-892
TOPIC TAGS: supersonic aerodynamics, hypersonic aerodynamics,
jet flow, gas jet, jet
flap, shock wave
ABSTRACT: A simple method i resented for determining the
deviation of supersonic
and hypersonic plane-paralleNplows of an invisci~~as_produced
by an auxiliary thin'
jet layer (jet-flap). This method is based on a formula derived
previously by
Carafoli which makes it possible to determine the pressure
coefficient in terms of the
deviation angle, and which may be applied either in the case of
compression behind a
shock wave or continuous expansion, over a wide range of
deviation angles. Approxi-
mate parametric equations for the jet trajectory and the
maximum range of variation
of the pressure coefficient, a
.and simplified formulas valid for small deviations re

ACC NR- AP6029839
derived. The results of numerical calculations presented in
graphs and tables are
given as illustrative examples. Orig. art. has; 4 figures, 44
fo-Lmulas, and
3 tables. [ABI
SUB CODE: 20/ SUBM DATE: 3011ay66/ ORIG REF: 005/ OTR REF: 006
7.
Cc d ?

L o8547-67 4P (w) /EVIP (k) IJP(c)
ACC NR. AP6035397
SOURCE CODE: RU/0008/66/023/005/1343/1353
AUTHOR: Carafolf, E.; Mateescu, 11.
ORG: Institute of Fluid Mechanicii, Academy of the Rumanian
Sociaj!jL Reputq_A.c
(ins tfEU'Cul-d6'-m'-e~d~i-~'a--iluidelor al Academiei Republicii
Socialiste Romania)
?b I t'
TITLE: The harmonic oscillatory movement of a win& conical body
system under
supersonic conditions
SOURCE: Studii si cercetari de secanica aplicata, v. 23, no. 5,
1966, 1343-1353
TOPIC TAGS: harmonic oqcillatiov, conic body, supersonic flow -
ABSTRACT: This work studies the non-constant suporsonic
QQ"r9_vnd_t_he _ing=p_
-w omjjc~aL
body system where the harmonic oscillatory movement is of low
frequency. Considering
case of the harmonic rotation oscillations of pitching and
rolling, as well as of
translation along the vertical axis, the problem is reduced
through analogy with the
case of detached wings to the study of constant conical movements
of the order of 1
and 2 around the wing-conical body Bystem. In order to determine
these, the authors
use the results obtained in theiv previous works. An expression of
the coefficient.--
of pressure is obtained wish a view towards ascertaining the
distribution of pres-
sures upon the system under conalderation. The problem studied
here is applicable
,to the development of supersonic aircraft. Orig. art. has: 51
formulas and 3
-figures.
SUil COW:,: 20/. SUBM DATE: '25Ma-r66/ ORIG REF: 006/ OTH REF: 00W
ATD PRESS:5104
uDc: 533
WWIEM

L 10017-67 EJVP W/EWP (W) /E Lqp (Nt Jjj~~L
ACC NRi AP6036267 %";OURCE CODE:
RU/(!(~lVf6'6-fO-fl-1005~/12Z9i-/123
AUTHOR: CarafolL,'! -Elie; Mateescu, Dan '51
ORG: Institute of Fluid blechanicalAcademy of the Rumanian
Socialist Republic
TITLE: Harmonic oscillatory motion of a wing-conic fuselage
system in a supersonic
flow V/
SOURCE: Revue Roumaine des sciences techniques. Serie de
mecanique appliquee, v, 11,
no. 5, 1966, 12219-1239
TOPIC TAGS: supersonic aerodynamics, conic flow, unsteady flow,
aerodynamic roll,
aerodynamic pitch, harmonic oscillation
ABSTRACT: The present paper is concerned with a study of
supersonic, unsteady floiia
over a wi R-conic fuselage system subjected to harmonic
low-frequencX oscillations
In this case, the motion of the wing-conic body system considered
here (Fig. 1) is*V
composed of the following three riotions: 1) harmonic oscillatory
pitch about the
Ox2-ax's; 2) harmonic oscillatory translation alon g the
Ox3-axis; and 3) hamonic
oscillatory roll around the Oxl-axis, assuming that.these
oscillatory motions are 'of
small amplitude and that the transverse dinwnsions of the
fuselage lire sufficiently
reduced with respect to the Mach cone. Thin problem is reduced to
the study of three
supersonic steady conic flows, two of which are pu .rIe conic
flows over a -Ang.-conic
body system, but the third is.a vecond-ordex conic flow over the
same system. -
Solutions for these flows can be obtained by using the method
developed previously
Card 1/3

T IA017-z
by the authors. The ;mial perturbation velocities for various
positions of the
leading edge of the wing with respect to the Mach cone were
calculated, and an
expression for the pressure coefficient in the cases of subsonic
and supersonic
Card 2/3

L 10017-67
ACC NR% AP6036267
leading edges was derived from these calculations. Orig. art.
has: 3 figures and
60 formulas.
SUB CODE: 201 SUBM DATE., 29K-ir66/ ORIG REFt 006/ OTH REF.- 0011
ATD PRESS: 5105
313 egk

ACC NR. AP7003247 SOIjRCE CODE RU/0019-/66/011/006/1365/1371---)
AUTHOR: Carafoli, Elie
ORG: none
TITIX: Application of quasi-conivil motions to the thcory of wings
with curved
leading edges
SOURCE: Rev roum scien techn. Ser mecan applp v. 11, no. 6, 1966,
1365-1371
i TWIC TAGS: supersonic aerodynamics, delta wing, conic flow, thin
wing, flow veloclt~6
pressure coefficient
ABSTRACT:
This paper deals with application of the so-called
quasi-conical'motions
to the theory of modern forms of aircraft wings. A detailed analysis
based on the author's previous work (Revue Mumaine des Sciences
Techniques-Mecanique Appliquee, v. 11, no. 6,'1965) concerning Ehe
quasi--
conical potential of motion around wings with subsonic curved
leading
edges is presented. An expression is derived for the quasi-conical
potential resulting from the aonical potentiAl corresponding to a
wing
with straight leading edges. Formulas are developed from this
expres-
sion for the axial disturbance velocity and the pressure
coefficient is
deduced for a flat wing with subsonic curved leading edges. The
results
Card 1/2 UDC: 536.421.1

WcCWR-: --A~-766*320
obtained here can be applied to wingd of'gothii-~ - shdpe
em-plo-y'ed in- s"u-p-ij-
sonic aerodynamics and the procedure may be extended to wings whose
central bodX.is.of arbitrary shape, to cruciform wi.ngs, etc.
Orig. art.
has: 2 figures and 42 formulas.
SUB CODE: 2 SUBM DATE: 05Apr66/ ORIG REF: 001/ ATD PRESS! 5112
So!

ACC NR- AP7003248
AUTHOR, Carafoli, E.; Staicu, S.
ORG: [Carafolil Institute of Fluid Mechanics, Academy of the
Socialist Republic
of Rumania; [Staicu) The "Gh. Gheorghin-Dej" Polytechnic Institute,
Bucarest
TITLE: Antisymmetric thin delta wing with flow separation at the
leading edges
SOURCE: Rev roum scien tecbn. Ser mecan appl, v. 11, no. 6, 1966,
1373-1386
TOPIC TAGS: supersonic aerodynamics, supersonic flow, delta wing,
flow separatioD,
vortex, conic flow, pressure distribution
ABSTRACT:
A supersonic flow around a thin antisymmetric delta wing whose two
halves
are at the same angle of attack but of.opppsite sign is considered,
with
flow separation taken into account. The effect of the flow
separation
at the subsonic leading edges on the flow pattern is investigated.
This. effect results in the occurrence of two concentrated vortex
nuclei of the same intensity and -sign having, however,
antisymmetric
position with respect to the axis of symmetry of the wing (see Fig.
1).
;Card 1/3

ACC NR% AP7003248
Fig. 1. Wing and flow
configuration

ACC NRI
;SUB CODE:
ATD PREM
AP10032148
The formation of vortices induces a complex field of
downwashes'which
alters tile flow in such a way that the pressures are finite at the
edges.,
The distribution of downwashes leads to a system of three
fictitious wings
whose superposition yields a resultant fictitious wing which is
equivalent,
e' to the real wing for Wiich tile axial dis-
from th aerodynamic standpoint, 0 1
turbance velocity has the expression: U = Ue + Ut Uc and which will
be
antisymmetric with respect to tile oxl-axis of symmetry and
continuous at the
origin 0. Since the flow remains conical, the pressures on the
upper and
lower surfaces of the wing and also the aerodynamic characteristics
may be
determined. Pressure distributions for various wings and different
angles
of attack at M = 1.9 and the variation of the rolling moment
coefficient
in terms of thZ angle of attack and various parameters of
slenderness of the
wing are presented in graphs for the cases of distributed and
concentrated
sourcer3. The. simplif ied case of a concentrated source is also
considered,,
Orig. art. has: 5 figures 'and 491oiviulas.
20/ SUBM DATE: 29Jun66/ ORIG REF: 003/ OTH REP: 003/
5112
3

,.CMGUO Ion
How the trade-union comittees execute their
Jurisdictional
attributionie Mum& sindic 6 mo.6:35-37 Jo 162.
P al comitstului sindicatului Fabricli de mape
1. Preoedi4
plastices, Pnuresti

CARAIANI, L.
Calculus of See-D?,-,e Throagh Jettieg of Homogenous
Earth in Unstationery
Regime. Hidrotehniop (Hydrotechr-clof-v), #4:1,?o:Aur~
57

C.
7 rl: all .DI--oj~-Uijj.
Petroic;um of :..oil
Re~"erai-m--, zhu7nc-l. no. :t
Y 12C ~,301, Inst, Petrol, ,-:~-Zc- Si r-eOl, v. o, 22',
Gener.al chcndcal charac teris tics and the checAc~d
co-,~:,)osition c~f
,,~otroloum, fractdon~- froni tho i.:oldova reizion ha it - b
e;-1 n i n %, o s tt c d.
4- -Id
-,-~ctroleiim has a hiJh --axaffin ccnten~ al: is hezwy
bucause of tho
contont of tar and aro%in-tic com-joiinds. The -petrolcvm
cont.iinz 0.4
T
Tile Iiht -fr:~ctions are chavacto:Azed 311 excess of aro:
atic
,y ainly cont~An nao1rithener, and oaraffins
,drocarbons un~l m, ill u."I'd r,
h
"'ns, but at t;,,C S%:,,kC '-i:nc
The heav,,- fractions consi~-A 0, P".r-
possess aronatic charact.o,~istics. The petroleur:
invest-,-atcd to
thc i)n-raffin-rai5hthene-arom--tic class. 2r-d
com-..unication zi-~G
1,961, 191,4134 -)fibstracter's note:' Cornplete
tr~tn~;L.-.tion.
bard 1/1

CREANGA, C.; WIVITREESCU, F., NEGRESCU, V.;
CARAIANI, V.; NEAGSUP
P.; RADULESCU, S.
Rumanian crude oil In the "Carpatica"
classification.
Rev chimie 7 no. 1: 111-1216 16-0.
1. Chaire de Chimie du Petrole Institut do
Petrole., do
Gaz et de Geologis Bucarest.

CARAIANI, V.; LEHESCU, C.; CREANGA, C.
Cyclohexans hydrocarbons in the lower
fractions of some
Rumanian crude oils in Muntenia and
Mol(~,via,- Bul Inst
Petrol Rum no. 1003-96 163.

ALEMDRESGU, I*, ings;_CARUMAN., Ghe, inge
NewAschnological method-in pisculture, the early
reproduc-
tion of carp. Ind allm anim 11 no.2t 46-49 P163
1. Directia generala a industriei pestelui.

CAMON, F.
Wrine Ostraco4a of the Mimenion waters of the Black Sea.
p. 89.
HIDROBIOLOGIA. (Academia Republici Populare Romins.
Comisie de Hidrologie.,
Hiditbiologle si lhtiologie) Bucuresti, Rwom4a. Vol. 1,
1958.
NDnthly list of Fast IDAropean Accessions (EM) LC, Vol.
8, no. 8, Aug. 1959
Unel.

KARAYON, Franchiska Yelena[C!raion, Francisca Elena]
-- -- I- ~ - . -
Now,speciesIof Ontracoda musoal In t ~~ 5lack Sea
(Bosporus watALrs).
Rev biol 5 no.1/2:iig-:i26 160. (Em .10:9)
(Black Sea) (Ontracoda)

CARAION, Francisca Elena
Loxoconcha bulgarica n.sp., a new ostracod col-lected
in the Bulgarian
waters of the Black Sea (Sozopol). Rev biol 5
no.):249-254 160.
(EW 10:4)
(RUMANIA--LOXOC(MCHL)

CARAION, Francisca-Elena
New Cytheridae (Omstgcea-Ostracoda) for the Fontic
fauna of
Rumania. Studii cerc biol anim 14 no.l.-III-M 162.
1. Comunicare prezentata de M.,A. lonescu, membru
corespondent
al Academiei R.F.R., membru a Comitetului de redactie
si
redactor responsabil, "Ectudii si cercetari de
biologie;
Seria biologie animala."

KARAYON, Franchiska Yelens, (Caraion, Francioca Elena]
Scme special probleas related to the present state of the
studies
of Ostracodain. in the Azov-Black Sea Basin, Rev biol 7
no*3:437w
449 162.
1. Institut biologii Ime Tr. Sevuleakus, Laboratoriya po
okeanologii Akademii RNR.

CARAION, Francisca Elena
Contributions to the Icnowledge of Potricola and OBtracoda
fa-ma along
the Rumanian littoral (Agigea and-Mangalia). Studii cerc
biol. anim
15 no.1:45-63 163.

CARATON, Fremcisca Elena
----
New representatives of the CytherVae (Ostracoda -
Podoeopa)
family ori"tin~g from the Rumanian Pontic waters.
Studii
cere biol izilm. 15 no,3%319-331 163,
1. Gomunicare-prezentata do M.A. Ionescus, membru
corespondent al
Academia R.P.R.

CAPAION, Francisca EJena
Observations on the OBtracoJa in the briny witter
anti Purersaline
brisina of the lbumanJan Black Sen littorul. Studli
cerv. biol ,.
zool 16 no. 4:271-')8'L 164.
1. Laboraotry of Anima2 Taxonomy, "T.i.-air-r.
instit..)te
of Biology.

CCKLMSCUp T., ing,; CARAMAN A irZo
Criteria for the tariffing of electric power as
reflected in
the policy of development of oil and chemical
industries,
in R%mmmia. Petrol. A gaze 13 no.7--321-325 J1
362.
1
1

CARAMAN, E., prof. inv. mediu (Bucurest3j
Application of the residue theorem. Gaz mat fiz
14 no.7:
352-358 i1 162.

GATALINJ F., ~llc . ~iTl*""41." 1. i i I; "
.1 1--X. : SEFBAN. M. .1 . -.
,6-2 ? f7,
r,-." p-A.1-clejua xa-"Ieries and the. teullnl~al
ard
.11
e-:~cnc-nic efl'ctF if thi:3 subst-t-iiti-n of the
enc-Irgy carrier
egant.. 'Petr,.-~! .91 nr?-,7e 15 Ja IN4.

CARLW, Phi~L., ing.
Econmic officacity In. directing railroad cars
according to
the polygon law. Rav eailor for 11 no,94WT-490 S
163.
1. Directia regionala Timisoaraw

Contributions to tbi Study of Fodlies of Inothermic Upersurfaces
Geoilesicany
ParaLUIL (lametric)
ran& do &saake;,
d semm"es Wisiqument pwand" Owl
R. P. Rondae. Fil . [a Stud.j
�ti. Wt. no. 2,191-20& ~(Rdrwisx.
i PAW
Rusibus and Fren4 swlin~
ric it
Rienumnien wie R, is cased isop"ainetrac it "tidies
th4 au~ Ad-W. Wbw At and A; M
Beftnini's fint-m'd ~- differtidw Pumultm 01 Re.
r6rhese hyperaw ces have been studled by UA-Civlta
;[Atti A.cc2d- Naz. Lincel. Rend. Cl. Sci. Fis. Mat. Nat,
126 (1937). 355-46;] and B. Sellve [ibid. 27 (1938).2D3-2071
in the case of euclidean spaceo and by E. Cartan [Math.
4S (W9)1 US-367] in the caw of Riemannian spaces',
lot constant caivature.
i In the present paper the author shows that the hyper-
1 surfacet Jn Ro imfilch are isothermic for the steady-&late
:andgeodesically parallel are identical with the family of'
Asoparmnetric hypersurfaces in R..
Ilew foHow a number of theorems concerning, mainly,
11arnities, of isolarametric- hypersurfaces in Riemannian
spaces, of constant curvature which are at the same time
;:Lamd f.
amilies, (i.e., they are part of an n-tuply prthogonal
sy#eul of hypersurfaces in R.).
The paper concludes with the consideration of a number
of particular cases of R3'S which admit families of iso

CARAMAN. Petru
The theory of the A-dimensional quasi-conformal
representations.
Rev math Pures 6 no.2011-356 161.

CAMIAN Potru
Theory of D-dimensional quasi-conformal representations.
Studii mat Iasi
12 no.1:13-52 161.

CA,RAMAV, Petru
The propertv N cf the n-dimensional
quasi-conformal represen-
tations. Studil mat Iasi 12 no.2.-227-248 161.

GARAMAR, Petru
Jacobi's method and the dilatations of
n-dinjensional
qUagi-conforml representations. Studii mat
Iasi 13
no.1:61-86 162.

CARAMAN, Petru
Existence theorems of n-dimenoional quasiconformal
representatioais,
Studii, mat Iasi 13 no.2:291-296 162.

CAIWUN, Pet-ru
On N'properties of n-dimensional continuous
representations. Studii
mat lasi 13 no.2:2W,-306 162.

GARLM&N) PO
On the n-dimensional quasi-conforml
representationso Studii
mat Iasi 14 no.ls9l-126 963.