U-2R AIRPLANE PROPOSAL

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00739R000400070006-6
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 4
• Document Creation Date: December 16, 2016
• Document Release Date: March 10, 2005
• Sequence Number: 6
• Publication Date: January 21, 1966
• Content Type: MFR

Approved For Release 2005/05/16 : CIA-RDP89B00739R000400070006-6
21 January 1966
MEMORANDUM FOR THE RECORD
SUBJECT : U-2R Airplane Proposal
Reference: (a) LAC Report No. SP-937, "Proposal for U-2R
Airplane"
(b) LAC Report No. SP=179, "Flight Test Development
of the Lockheed U-2C Airplane"
(c) Flight Manual for Models U-2C and U-2F
Aircraft dated 15 December 1965.
1. Viewing the reference .(a) proposal strictly from
an aerodynamic and performance standpoint, the U-2R represents
a modification to the U-2C. The primary goal of the modifi-
cation is to take advantage of the increased thrust of the
J75P-13B engine in the form of an increase in cruising
altitude before reaching the stall/mach buffet boundary. To
do this, it is proposed to increase the wing area from 600
square feet to 1000 square feet thereby generating the
necessary lift at a lower lift coefficient and hence avoid
the stall/mach buffet boundary. Although the theory and the
approach are reasonable, the complete lack of both aero-
dynamic and engine data precludes an independent analysis to
confirm the final results. However, assuming that the
Lockheed performance calculations are correct, certain
observations can be made.
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2. Reference (b) and (c) present flight test results
and flight manual data for the U-2C with wing slipper tanks.
A comparison between these data and the U-2C performance
presented in reference (a) reveals differences which can be
significant unless resolved. Specifically, figure 5 of
reference (a) presents a maximum altitude range mission of
the U-2C of 3000 n.m. with the altitude varying from 66,000
References (b) and (c) on the other
3470
compared
The U-2R cruises at
31/70
to the U-2C range of n.m.
Reference (a) also presents a 3000 n.m. U-2R mission at a.
reduced gross weight with the altitude varying from
0
It should be noted that the U-2C at
hand state the U-2C maximum altitude range as 3$-58-n.m. with
an altitude variation from 66,000 feet
Comparing this U-2C performance with the U-2R performance, for
the normal take-off weight, the altitudes are very similar
and the only substantive performance difference is the U-2R
25X1 range of
a reduced gross weight would show a corresponding increase
in initial cruise altitude.
3. The overload take-off weight for the U-2R is 36,750
pounds. This configuration includes fuel in the inboard wing
as well as the outboard wing. In this configuration the
initial cruise altitude for the maximum altitude mission is
64,000 feet and does not reach 70,000 feet until 2750 n.m.
25,
25
25
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have been flown. The total range for this mission is 25
n.m. The maximum range for the overload weight is 25
but, at best, can probably be viewed only as a ferry mission
since the entire altitude profile extends only from 55,000
to 69,000 feet. It should'be noted that all ranges are
based on zero fuel at the end of the mission. Consequently, any
realistic profile will result in both a reduced altitude and
a reduced range.
4. In order to fully evaluate the validity of the
performance estimates of this proposal it is necessary to
have the flight test drag of the U-2C, the estimated drag
increments between the U-2C and the U-2R and complete installed
engine performance. In addition, the proposal is completely
lacking in data for any of the sub-systems, such as, naviga-
tion, auto-pilot, hydraulic, electrical, etc. If these are
identical to the U-2C, it should be so stated.
5. In summary, there do not appear to be appreciable
performance gains for the U-2R over the U-2C. However, one
very significant improvement is that the U-2R will not be
flying in the stall/mach buffet corner thereby significantly
improving the handling qualities.
25
SECRET
Approved For Release 2005/05/16 : CIA-RDP89B00739R000400070006-6
 Approved For Release 2005/05/16 : CIA-RDP89B00739R000400070006-6
RANGE COMPARISON OF U-2R AND U-2C
U-2R
Zero Fuel Weight - Lbs.
Fuel Weight - Lbs.
Take-Off Weight - Lbs.
U-2C
Partial Normal Overload From U-2R U-2C Flight
Fuel Fuel Fuel Proposal Manual
17,400 17,400 17,400
9,390 12,730 19,350
26,790 30,130 36,750
12,890
10,166
23,056
Maximum Altitude Range - N.M.
Cruise Altitudes - Ft.
Maximum Range - N.M.
Cruise Altitudes - Ft.
3,000
55,000 -
69,000
3,000
12,890
10,166
23, 056
31170
25X
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