SCIENTIFIC ABSTRACT MATEESCU, D. - MATESCU, S.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001032820007-8
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: June 14, 2000
• Sequence Number: 7
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

R/00YB60/000/%P/Ool /009
A general method for determining D256 J)301
2K 2 /(L - X)(Tj + S) K 2
(s - L-) arg ch ~ - -L (s + -2-) arg ch
x V 2L(S - X) it x
22 a arg ch (L X2)(S2 - 4c (95)
VT(Ls;:--::,
v _211US -+-X-Y-- x X (s2 X2 M 2 _ 4c2
in which 14 and K are expressed by
(U0 - OL 2) U` (062 061 ) U,
V1 - B2c2 K V1 - B 2 82 (96)
If the leading adges are supersonic and the trailing edges subso-
nic the solution is expressed bys
X + 2C)
ru incI arg ch (97)
( 2 Pe - X)
Card 16/35 _ff

2o5614, .
R/008/6o/ooo/bo1/oo1/ooq
A general method for determining ... D256/D301
2n + + X) + 2,)
arg oh
2
(2c + X)
2x( -X (-L+S
7r oh
2
(S - JO (97)
2X +X +S
8 + ch HT
7f firg - -----
(S+X)
20 aro* 43 +L
08
7r
(L X)
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2o564
R/008/60/000/001/001/009
A general method for determining ... D256/D301
+ -L+L
20
- I+ are Cos
79 2 (L + X)
B
X11) (S' - 40)
F.0 2 2
arg oh
(S2 ~ xr) 4 (97)
W 13)
X-) (LI-40)
Bro Cos (97)
x 7r (Ls - X2) 40)
in which and K have the values from (96), and Q is:
Q Ot i U (98)
Card 18/35 -\62 12 - 1

20564
R/008/60/000/001/001/009
A general method for determining D256/D301
where the leading and the trailing edges are supersonic the solu-
tion is:
+ 2,)
1~ ru ix-c (1 arg ch X)
2
_~x (2c - X)
+
+ x)(, + 2c)
0 + R) arg ch is - -
x 2 (2c + X)
(99)
FT
+ S)
X,
V(7-,
2r ~22 x)(,
(a - are cos
x 2 (S X)
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20564
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A general method for determini-ng ... D256/D301

* 2 + S)
+ X)
=3
=
2K
(s + a
are cos 2
2
1

qj
x

+ X)
(S + X)

2Q
Ii B
- 6,7.,a (10B
I -
(L - X)
+L
(-(BL X) L
20 C2

W 2

X.) (S2 - 40)
ixe K*c2 2 are 13
-- 00
2 R (s2- x1r) -4
Card 20/35 L
(99)

A general method for determining ...
Xs) (L3 4e2)
RC-1 I. are 00 eB 2 -'
(LI - 41.
20564
R/008/60/000/001/001/009
D256/D301
(99) (99)
in which Q and x have the values from (98) and (96), and K' is:
..K. = (%-Ctl)U. (100) (100)
iris -I
The authors theii determine the motion around the conical fuselage-
symmetrical thick wing Systems by considering that the fuselage
axis and the wing have no angle of attack against the non-distur-
bed flow. In the x plane, the boundary conditions on the circle of
a c radius are the same as in case of the fuselage-thin wing sys-
tem, the fuselage having no angle of attack. The boundary condi-
tions on the wing and the rest of the oy axis beyond the wing are
the same as in the case of an isolated thick wing. The disturbance
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20564
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A general method for determining ... D256/D301
speeds have the same peculiarities on the leading and trailing ed-
ges of the wing, as in the case of the isolated thi-ck wing. The
motion of the upper semi-plane around the fuselage-symmetrical
thick wing system is equivalent to the motion of the upper semi-
plane around the fuselage-thin wing system where: a) the wing has
supersonic leading edges in Al (x = 1; >Amax Z-.1, 1,-7) and A'
B 2
(x I min as shown in Pig. 4; b) the fuselage
791 - 12-7)1
has a zero angle of attack; c) the wing has the angle of attacks
~i and ~vj on different sections of the A,Nl and A2N2 segments re-
spectively, and a zero angle of attack on the A~A2and AlAj sec-
tions (Fig. 4). Thus, the problem of flow around the conical fuse-
lage-thick wing system was reduced to the flow around the conical
fuselage-thin wing system. The axial disturbance speeds of the mcre
interesting cases are presented as follows: a) In case the wing
has the � T, slopes on the Alm, and A2M2 sections, respectively
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20564t
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A general method for determining D256/D301
�,V, slopes on the MjNj and M2N2 sections, and if the wing pre-
sents a geometrical symmetry against the fuselage axis, i.e. if
11 = 12 = 1t and s1 = B2 = a. the solution in the case Of subsonic
leading edges is given by:
(I ch
-2
(L - X)
2
1 + (101)
+ arg c
x hT~_2_
I (I + X)
2 x)(I + S)
2K c I M N
% (a - _F) arg eh 197-1
Card 23/35 9 (S - X)
F7B

A general method for determining
2o564
R/008/60/000/001/001/009
D256/D301
+
2
2K
+ 2 ) arg chj~-2-
T x S + X)
2c)
X) +
arg ChV -75-
2 X
it x S (2c -
2-Kc (1 +.2) arg ch + X)( + 2c)
7t x ~(2c+ X)
x2 (Lf 4,
ixe 2 _ go22 arg c 7 1
x x 77 (L2 X2) :_2 402)
Card
(101)

A general method for determining
( 1
2 -7 '
Kc 2 arg oh B
I_B(_S7
x 7t (s2
20564
R/008/60/000/001/001/009
D256/D301
X2)(f;2 4c 2
(101)
- 2)(1 7T,-
X - 4c
B7
in which Q. K, and K are expressed by:
Or, _-Y.) U- I 'K (Y2 - YOUM. X YUC. (102) (102)
V, __JrP vi - )PSI V1 - ire,
If the leading edges are supersonic and the trailing edges subso-
nic, the solution is the same as in case of the conical fuselage-
thin wing system, i.e. Eq. (97), in which ixl andO62 are replaced
by y., and V2 respectively. If the leading and trailing edges are
supersonic, the solution in expressed by Eq. (99), in which obj and
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A general method for determining ... D256/D301
012 are replaced by X, and ~2, respectively. b) If the whole wing
has a 1 y slope, having no symmetry against the fuselage axis, the
solution in case of subsonic leading edges is given by
+
20, X) (S
-(h - -3) argoh 1B L
7W X 2
V (LI - X)
20, + X) + L-) (103)
to + -!f W9 Oh
Z) 2
(LI + X)
X) + 2,)
2X*C oh
X) -L (2c - X)
V
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A general method for determining
20564
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D256/D301
W-+ X) ~'g'+ 2r)
+ t arg ch
2 2
(2c + X)
X2
40
LXLO
K (k) - F k'
)-r
+ c
+2C
4cs
+ 2c
11 i~t, (103).
x-+ c p
IN
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(103)

20564
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A general method for determining ... D256/D301
in which QlCl on the segment 2-1 ~_- X = y < and 0 be-
x
yond this segment; V = Q2 C24 on the segment - `_X y
2 x 29
and 0, beyond this segment, in which Q and x are expres-
2 19 Q2
sed by
YUM I Q2 = YUM X= yuct
~-- 1 (104)
B2,, (104)
and k. Ti and 72 by
k (I - P= (1058) (105 a)
(l + B0% (I +.BC)I(X - C)"
and (1 + Bc)(11 - 0) (1 + Bc)(12 - 0
Cf 1 = are sin 1 Be) -(11 +0) 1 CF2 are sin (1 - Be)(12 + C)
Card 28/35 (105 1)

A general method for determining ...
2o564
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D256/D301
If the Al leading edge is supersonic and the A2 leading edge sub-
sonic, the solution is given by
L
x + L,
20', (B -
aro '00', V
(LI - X)
+
1. + arg ch X)
79 S) 2
V (L2 + JO
_L_X -L+2c
2x*c arg oh
2
(106)
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2o564
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A general method for determining D256/D301
2x'ct:t + + x + 2c
arg oh
2 (2c + X)
20 (106)
ix*cs
[2xF(?;, k1)+
z nz x - c
+ 2c
+ + c 2c) H (,p;, pl, )4) 1~ X.
I w z - c- K (k) -
I -L + 2e
F (%, k) - ' I . -t I k 0
S+c p p (106
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20564
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A general method for determining D256/D301
Q-W02
in which f 21 on thLe segment