OXCART DATA

• Document Type: FOIA
• Collection: FOIA Collection
• Document Number (FOIA) /ESDN (CREST): 06452664
• Release Decision: RIPPUB
• Original Classification: U
• Document Page Count: 2
• Document Creation Date: December 28, 2022
• Document Release Date: February 9, 2017
• Case Number: F-2015-02619
• Publication Date: December 31, 1959

Approved for Release: 2017/02/03 006452664
OXC-0201
OXCART DATA
31 December 1959
Aircraft Dimensions:
Length
Height
Wing Span
Wing Area
Wing Configuration
NaceERConfiguration
Gross Weight
Fuel Weight
98 3/4 feet
18 1/4
59
1,795 square feet
Delta
Mid-wing
112,000 lbs.
60,000 lbs (less reserves)
Aircraft Performance (as of 17 August - see attached
Basic mission begins with climb and acceleration after subsonic
refueling at 35,000 - 40,000 feet.
Cruise Speed
Cruise Altitude
Start
End
Cruise Range
Mach 3.2
84,500 feet
97,600 feet
4,115 n. ml (Including climb and
descent)
Basic mission is proceeded and followed by supersonic cruise legs of
somewhat more than 4,000 n. ml each at cruise altitudes between
78,000 to 87,000 feet. Total flying time, including two (2) aerial
refuelings,is approximately nine (9) hours maximum.
Extreme mission is similar to basic mission except two (2) penetration
legs at 84,500 - 97,600 feet altitude are accomplished interrupted by
subsonic air refueling outside enemy territory. Total time, including
three (3) air refuelings, just under 12 1/2 hours maximum.
(b)(1)
Approved for Release: 2017/02/03 006452664
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Approved for Release: 2017/02/03 006452664
Special Items: Engine - airframe design:
1. Engine augmentor: Because of mid-wing nacell2design, the augmentor
at aft end of nacelle must be part of basic wing structive. Prime respons-
ibility remains undecided but Lockheed Aircraft Corporation now wishes
to do this.
2. Engine jet exhaust ionization: In order to minimize radar
return from engine tail pipes, a special fuel tank containing a
fuel slurry of potassium or other salts is needed to feed into the
afterburner during basic combat leg of mission. This slurry is in
addition to regular fuel normAlly burned in afterburner and is not
used on inbound and outbound legs.
3. Increase in speed from Mach 3.2 to 3.5. The higher speed is
expected to allow an increase of at least 3,000 feet in cruise altitudes.
The airframe is being designed and tested structurally and aero-
dynamically (except for nacelle air inlets and augmentors) to Mach 3.5.
Lead-time and cost of Mach 3.5 engine may dictate changes in planned
quantity and delivery schedule of Mach 3.2 versions.
4. Engine, afterburner, and nacelle inlet control: Close integration
of control functions must be maintained due to extremes in dynamic
pressures and temperatures encountered during mission. Since Hamilton
Standard are to supply basic engine-afterburner controls to P & W
and inlet control to Lockheed, this seems to be in hand.
5. Engine accessory drive: The power take-off drive requires redesign
due space limitations in the engine nacelle.
Attachment:
(b)(6)
E. P. KIEFER
SA for TS
(IN14443) (b)(1)
Encl f2 or oxC-0100 cy 1 Of 1
DPD-DD/P:EPKtubER:amcb
Distribution:
--0 - DD/P w/att
2 - Ch/DB-DPD wo/att
1 - RI-DPD wo/att
2
Approved for Release: 2017/02/03 006452664