U-2R STANDARD AIRCRAFT CHARACTERISTICS CHART

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00739R000400160006-6
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 10
• Document Creation Date: December 21, 2016
• Document Release Date: April 17, 2008
• Sequence Number: 6
• Publication Date: September 13, 1966
• Content Type: MFR

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Copy-.of
13 September 66
MEMORANDUM FOR THE RECORD
SUBJECT : U-2R Standard Aircraft Characteristics Chart
REFERENCE : LAC Report SP-937, "Proposal for U-2R
Airplane", 27 December 1965
Attached herewith is one copy of the U-2R Standard
Aircraft Characteristics Chart prepared by ASD/D/R&D/OSA.
This chart represents the ASD/Lockheed estimated performance
of the U-2R aircraft for the exact configuration as proposed
in the reference report. It does not include the various
It does
include the current off-the-shelf payload con igura ion as
used in the U-2C. Subsequent revisions to this chart will
be prepared and issued as the program progresses and more
data become available.
epu y for
Research and Development
Special Activities
APD/OSA ca (13 Sept 66)
Attachment - 1
As noted above
Distribution:
1 - D/R&D/OSA w/att
2 - D/SA w/att
3 - DD/SA w/att
4 - D/O/OSA w/att
5 - D/M/OSA w/att
6 - IDEA Div/O/OSA w/att
7 - ASD/OSA w/att
8 - PSD/OSA w/att
9 - SSD/OSA w/att
10 - ASD/OSA (Chrono) wo/att
11 - RB/OSA wo/att
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TOP S"KLT
TnP SFIRFT
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is
MENMEMEN 0000"
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PF r)POSED 25X1
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PO" ER PLANT
Nbr. & Model ..... (1) J75P-13B
Mfr ....... Pratt & Whitney A/C
Engine Spec Nbr. N-2614G
Appendix B
Type ..... ...........Turbojet
Augmentation............. None
Length............. 132.62 In.
(Not Including Tailpipe)
Diameter (Max Flange)
42.94 In.
Weight Dry (Spec)...4,960 Lbs
RATING
Condition Thrust SFC
S.L.S. 17,000 lbs. .82
ELECTRONICS
Comm. & Nav. Systems
AN/ARC-34........... UHF Radio
AN/ARC-51 ..........UHF Radio
618-T............. HFSSB Radio
AN/ARC-59 Radio Compass (ADF)
ARC Type 15F, ........ (VOR)
914-1 (Wilcox).... .... .IFF
ARC-12 -------- .
____UHF Radio
IV] SSION AND DESCRIPTION
The mission of the U-2R model air-
plane is to perform aerial photo and
electronic reconnaissance.
The U-2R is a single-place, single
engine aircraft built by Lockheed
Aircraft Corporation. The airplane is
an improved design which utilizes the
salient features of the U-2C model.
The improvements made have been in the
use of a larger wing, higher thrust
available, increased payload flexibil-
ity and higher fuel capacity. The
improvements in the wing, thrust and
fuel capacity have enabled the U-2R to
have higher altitude capability, range
and speed than its predecessor, the
U-2C. This airplane has the necessary
provisions for operations from naval
aircraft carriers
DEVELOPMENT
Proposal ............... 27 December 1965
25X1
WEIGHTS
oa ing Lbs. L.F.
Empty... ........... 15
Zero Fuel ....... 17,400*
Normal T,O...... 30,130** 2.5
Overload T.O....36,750+ 2.0
'"Includes 100 lbs. of unus-
able fuel and 945 lbs. pay-
load.
Zero fuel weight plus
12,730 lbs. of fuel
+ Zero fuel weight plus
19n 1 he of f?P1
FUEL AND ON
FUEL
LOCATION GALLONS
Normal Wing Fuel ...... 1,935
Overload Wing Fuel 1)006
Spec ........ MIL-J-5161E (ASG)
25X1 OIL
9 gallons
Spec .............. MIL-L-23699
PHOTO-SENSORS
Proposed photo-sensors and
characteristics are shown on
separate page of this docu-
ment.
DIMENSIONS
resented in Lockheed pro-
posal and do not represent
contemplated U-2R defensive
systems. Subsequent charts
to be published reflecting
U-2R defensive systems
capability.
Wing
Span ............ 103 Ft., 91,8" folded
Area ............. 1,000 sq, ft.
Thickness, . .... , 9700 (Root) 6%C (Tip)
Aspect Ratio........... . 10.67
Length..... 62 Ft. .........1.0 In.
Tread ............................50 Ft.
I -AUGUST 1966 TOP SECRET U-2R
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 PERFORMANCE SU'' 1ARY
TAKE-OFF LOADING CONDITION
OO
TAKE-OFF WEIGHT lb.
30,130
26,790
Fuel internal/external (B) lb./lb.
12,730/-
9)390/-
Payload lb.
945
945
Wing loading lb./sq. ft.
30.13
26.79
Stall speed--power off (C) kn.
89.5
84.5
Take-off run at S.L. - calm ft.
L 000
782
Take-off run at S.L. -25 kn. wind ft
560
420
Take-off to clear 50 ft. - calm ft.
1 730
1,432
Max. speed/at maximum altitude kn./ft.
413/Max, Alt
413/Max. Alt.
Rate of climb at S.L. fpm
5 775
6,520
Time: S L to 65,000 ft. Hrs.
0.68
0.54
Tim : S L to May Initial Alt Hrs.
L l
1.1
Max, Initial Altitude ft.
68,200
Rnnge (A) n.mi.
3,959
2 793
Average Cruising Speed M/kn.
0.72/413
0.72/413
Max. C r y ' ng altitude(s) ft.
8 2 0
n.mi hr.
1979/9.7
1396/6.8
Average cruising s eed M/kn?
0.72/413
0.72/413
LANDING WEIGHT lb.
Fuel lb.
987
987
Sta11 Speed-nwe-2ff/._)Pr. ~h-PQWer(C)/(D)kn/kn
70/64 8
70/64.8
Landing distance over 50 ft. obst/ground rollft/ft
169042
1690/942
A. No credit for descent distance
B. Fuel density 6.58 Lbs./Gal.
C. Flaps Up
D. Flaps Down 35 Degrees Performance Basis: Estimated
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1 Auo-ust 1966 TOP SECRET U-2R
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 I f
V
2
.
a_ 26 21
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CLIMB
20
10
S.L
TAKE-OFF
4 14L 41 ~j
_11
-+ -T
i ~
~
i
k
c?f U41 -K
29 30 31 32 33 34 35 36
Gross PVeight-1000 Lbs.
1 August 1966
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V CRUISE-CLIMB OUT
ors, - .. .?s_
vd ?~ CRUISE-CLIMB IN
moo,
v?~"?~??pU- PENETRATION ALTITUDE
TOP SECRET
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