PROJECT HAZEL AERODYNAMICS REPORT NO. ZA-282 OCTOBER 1958

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00709R000400820001-4
• Release Decision: RIFPUB
• Original Classification: S
• Document Page Count: 73
• Document Creation Date: December 27, 2016
• Document Release Date: December 13, 2010
• Sequence Number: 1
• Publication Date: October 1, 1958
• Content Type: REPORT

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COVER SHEET FOR SECRET MAIL
This document contains information affecting the
national defense of the United States within thc
meaning of the Espionage Laws. Title 18, U.S.0
Sections 793 and 794. Its transmission or the rtyelatioi
of its contents in any manner to an unauthorizei
person is prohibited by law.
mum
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?SECRET
PEROMEAV
AERODYNAMICS
REPORT NO. ZA 282
OCTOBER 1958
ON VAI R
DIVISION OF GENERAL DYNAMICS CORPORATION
SAN DIEGO, CALIF
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C 0 N VA I R REPnRi ZA-282
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DATr 10/27/58
SAN DIEGO
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TITLE
PROJECT HAM
Aerodynamics Rri .1t/41';' /51 gin
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Report EA-2/12
Date 10/27/58
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PREPARED BY (7 (
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GROUP AERODYNAMICS
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C. J Cohan
,ec:,, REFERENCEN0a8-58-832(133-100)
M. G. D'Aununzio
CHECKED BY & f?
"iVii APPROVED BY
V
E. Piper D. H. Bennett
Chief of ,.. 111 ?"atievinc
NO. OF PAGES 111M...../...
NO. OF DIAGRAMS
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REVISIONS
NO.
DATE
BY
CHANGE
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PAGES F CTEIJ
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ANALYSIS
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CONVAIR
A DIVISION OF GENERAL DYNAMICS CORPORATION
1 SAN DIEGO)
PAGE A
REPORT NO. ZA-282
MODEL Hazel
DATE 10/27/58
SECRET
FOREWORD
This report is presented as one of a set describing the
Project "Hazel" study performed by the Convair San Diego
Division of the General Dynamics Corporation. The entire
set of reports, listed below, represents Convair's fulfill-
ment of the publications obligation specified in Contract
NOas-58-812 (SS-100) and Amendment #1, issued 14 August
1958 by the Bureau of Aeronautics.
ZP-252 Summary (Brochure of Charts with Text)
ZP-253 Aircraft Design
ZA-282 Aerodynamics
ZJ-026 Propulsion, Structure Heating, and Pressuri-
zation
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ANALYSIS
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CONVAIR
A DIVISION OF GENERAL DYNAMICS CORPORATION
SAN DIEGO)
PAGE ii
REPORT NO. ZA-282
MODEL Hazel
DATE 10/27/58
SECRET
SECURITY NICE
This document contains information
affecting the national defense of
the United States within the meaning
of the Espionage Laws. Title 18,
U.S.C., Sections 793 and 794. Its
transmission or the revelation of
its contents in any manner to an
unauthorized person is prohibited
by law.
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ANALYSIS
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CONVA1R
A DIVISION OF GENERAL DYNAMICS CORPORA1 ION
I SAN DIEGO)
PAGE iti
REPORT NO. ZA-282
MODEL Hazel
DATE 10/27/58
Foreword
SECRET
13r4.BIE air COMMITS
Security Notice
List of Figures and Tables
List of Sysibols
Summary
Introduction
Discussion
1. Types of Vehicle Studied
2. Aerodynamic Design Limitations Imposed by Operational
Requirements
3. Trajectories
4. Ramjet Powerplant Characteristics
5. Aerodynamics
6. Vehicle Sizing
7. Configurations
8. Maneuverability
9. Parametric Studies
Appendix A
Lift
Pitching Monent Characteristics
Longitudinal Control Requirements
Selection of Longitudinal Control
Tip Control Characteristics
SECRET
2
3
4
5
6
9
9
11
11
13
15
15
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A DIVISION OF GENERAL DYNAMICS CORPORATION
SAN DIE(.,O)
PAGE iv
REPORT NO. zik...282
MODEL Hozei
DATE 10/27/58
/011164 I II 1 -^-1
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TABIE 07 COWES (Cont'd.)
Control Size 16
Control Balance 17
Drag at M 3.0 17
Lift to Drag Ratio, LiD 20
Directional Static Ste:bility 20
References 22
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ANALYSIS
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SAN DIEGO)
PAGE y
REPORT NO. ZA-282
MODEL Hazel
DATE 10/27/58
SECRET
FIGUIES
Figure No.
1 mc-lo 3 View 26
2 me-19 3 View 27
3 MC-20 3 View 28
4 mc-24 3 View 29
5 PC-22 3 View 30
6 Pc..24 3 View 31
7 Rocket Configuration 32
8 mc-lo Trajectory 33
9 Marquardt Ramjet Characteristics - Pentaborane 34
10 Marquardt Ramjet Characteristics - SF-1 35
11 Marquardt Ramjet Off Design Characteristics - Pentaborane 36
12 Marquardt Ramjet Engine Weights 37
13 Marquardt Ramjet External Drag Characteristics . 38
14 Pratt and Whitney Ramjet Characteristics - Pentaborane . 39
15 Pratt and Whitney Ramjet Characteristics - SF-1 . . . ? ho
16 Wing Structure Weights 41
17 Turn Capabilities 42
18 Effect of Starting Altitude on Vehicle Gross Weight . ? 43
19 Effect of Fixed Weight Changes on Vehicle Gross Weight ? 44
20 Range Parameter as a Function of Altitude 45
21 Wing Alone Characteristics 46
22 Lift and Pitching Moment Characteristics 47
23 Lift Due to Control Deflection 148
24 Lift Effectiveness as a Function of Control Size . . . hn
? -.7
25 Control Effectiveness and. Aerodynamic Center 50
26 Control C.P. Position 51
27 Control Force and Center of Pressure 52
28 DYW Speed Trim Characteristics 53
29 m . 3.0 Trim Characteristics 54
30 Trim and Anti-Balance Tab Schematic 55
31 Tab Effectiveness 56
32 Trim Lift and Drag Characteristics 57
33 WD as a ?Unction of Lift Coefficient 58
34 Yawing Mdment Coefficient Slope 59
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ANALYSIS
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y4.
REPORT NO. 7A-282
MODEL Hazel
DATE 10/27/58
Table No.
SECRET
TABLES
Basic Characteristics of MC-10
II Basic Characteristics of Hazel Configurations 23
(Ramjet Cruise)
UI Basic Characteristics of Rocket Povered Hazel 24
Configurations
IV MC-10 Zero Lift Drag Breakdown 25
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A DIVISION OF GENERAL DYNAMICS CORPORATION
SAN DIEGO)
PAGE vii
REPORT NO. ZA-282
MODEL Hazel
DATE 10/27/58
SECRET
SYMBOLS
A3= engine reference area - ft2
A6= engine exit area - ft2
Ac= capture area - ft2
PD = drag coefficient
CBI induced drag coefficient
zero lift drag coefficient
CDO =
AqiNerp increment in CD due to wing warp .
CL 0 lift coefficient
Clats- = lift coefficient due to control deflection - 1/deg.
CM control effectiveness - 1/deg.
PM = pitChing moment coefficient
CM? pitching mcment coefficient at zero lift
Cs ? normal force coefficient
Cn = yawing moment coefficient
Cn(3 = yawing moment coefficient slope - 1/deg.
c.g. = centeroaf4ravity
c.p. = center of pressure
-e" or MAC = mean aerodynamic chard - ft.
load Factor - acceleration of gravity
H. M. 0 control hinge moment - lb-ft.
reference length ? root chord - ft.
L/D 0 lift to drag ratio
MA moment of,ares. ft3
MechJnneber
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C 0 N VA I R PAGE Vial
OF GENERAL DYNAMICS CORPORATION REPORT NO. 7A-282
( SAN DIEGO)
MODEL Hama
DATE 3427/58
ANALYSIS
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P a pressure - lbs/ft2
q a ,dynamic pressure - lbs/ft2
RN a Reynolds nudber
Sm. a wing area - ft2
8V
Sc
a fin area -ft
2
a control surface area - ft2
sr-1 = liquid hydrogen
SL.E. leading edge cross sectional area - ft2
SB a wing base area - ft2
SFC a specific fuel consumption - lb/hr/lb
ST area of control tab - ft2
t/c = thickness ratio
^ 0 velocity - ft/sec.
V a average velocity during cruise on first 1/3 of fuel - ft/sec
V
a average velocity during cruise on last 2/3 of fuel - ft/see
4x distance along X axis from c.p. to e.g. - ft.
Xa.c. a distance from leading edge of MAC to aerodynamic center - ft.
X0.p. a longitudinal distance from leading edge of MAC to the point
through which the resultant aerodynamdc force acts - ft.
Xe.g, n icingitwitruti distance from leading edge of MAC to e.g. - ft.
WO a initial weight - lbs.
Wi weight with 1/3 of fuel consumed - lbs.
W2 a weight with all fuel consumed - lbs.
Wi = weight of propellant - lbs.
angle of attack of root chord - degrees
0'1 = trim angle of attack - degrees
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PAGE ix
REPORT NO. 2A-282
MODEL Hazel
DATE 1027/58
SECRET
6 . control surface deflection - degrees
4.r . control surface deflection required for trim
3 . sideslip angle - degrees
I" = ratio of specific beats
AL.B. ' sweepback angle of 'wing leading edge - degrees
- degrees
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PAGE
REPORT NO.
MODEL
DATE
ZA-282
Hazel .
10/27158
SECRET
&MARY
This memorandum presents the aerodynamic characteristic, performance
and methoda of analysis used in the study of several manned reconnaissance
vehicles.
Studies were made to size a number of configurations to yield ranges of
3,200 or 4,000 nautical miles carrying payloads of 300 to 1,300 lbs. A basic
configuration designated MC-10 vas selected and a more detailed analysis of
lift, drag, stability, control and maneuverability vas made.
The basic characteristics of MC-10 are included in Table I.
Payload
Range
Cruise
Cruise altitude
Weight and start of cruise
Fuel (Pentaborane)
Lift/drag at start of cruise
Reference (wing) area
Engine - 1 Marquardt ramjet
TABLE I
lbs.
Mach number
ft
lb
lb
L/E
ft
800
3,200
3.0
125,000 to 137,800
13,800
6,330
4.17
1,985
The 4C-10 meets or exceeds the performance requirements stated on
page 1 of this report.
A three-view of MC-10 is shown in Figure 1.
Additional configurations are shown in Figures 2 through 6.
The basic characteristics of a nuMber of ramjet cruise configurations
are alum in Table II.
Velocities required of boost-glide and boost-rocket cruise-glide type
vehicles were found unacceptable by the customer. As a result these
configurations are included for record purposes only and are not discussed
in detail.
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ANALYSIS CONVAIR PAGE 1
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CHECKED BY MODEL Hazel
REVISED BY DATE 104-27'"58
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INTRODUCTION
The purpose of the work summarized in this memo was to conduct a
preliminary study of a manned reconnaissance vehicle, either glide or
cruise, to meet the following requirements:
Reconnaissance altitude 150,000 to 200,000 ft
(100,000 ft. minimum) .
Cruise speed (if cruise type) Mach No. 2 to 3.
Glide speed (if glide type) as low as possible
Range 3,200 n.mi. (2,500 min.)
Reconnaissance range at optimum altitude 1,500 n.mi. (1,000 min.)
Payload 800 lb. (Iwo minimum)
Crew 1
Seabesed
Wing loading,