Lockheed U-2

Specifications

1st Flight 1964

.Crew: 2; Pilot and reconnaissance systems officer (RSO)

Length: 107 ft 5 in (32.74 m)

Wingspan: 55 ft 7 in (16.94 m)

Height: 18 ft 6 in (5.64 m)

Wheel track: 16 ft 8 in (5 m)

Wheelbase: 37 ft 10 in (12 m)

Wing area: 1,800 sq ft (170 m2)

Aspect ratio: 1.7

Empty weight: 67,500 lb (30,617 kg)

Gross weight: 152,000 lb (68,946 kg)

Max takeoff weight: 172,000 lb (78,018 kg)

Fuel capacity: 12,219.2 US gal (10,174.6 imp gal; 46,255 l) in 6 tank groups (9 tanks)

Powerplant: 2 × Pratt & Whitney J58 (JT11D-20J or JT11D-20K) afterburning turbojets, 25,000 lbf (110 kN) thrust each

JT11D-20J 32,500 lbf (144.57 kN) wet (fixed inlet guidevanes)

JT11D-20K 34,000 lbf (151.24 kN) wet (2-position inlet guidevanes)

Performance

Maximum speed: 1,910 kn (2,200 mph, 3,540 km/h) at 80,000 ft (24,000 m)

Maximum speed: Mach 3.32

Ferry range: 2,824 nmi (3,250 mi, 5,230 km)

Service ceiling: 85,000 ft (26,000 m)

Rate of climb: 11,820 ft/min (60.0 m/s)

Wing loading: 84 lb/sq ft (410 kg/m2)

Thrust/weight: 0.44

Avionics

3,500 lb (1,588 kg) of mission equipment

Itek KA-102A 36–48 in (910–1,220 mm) camera

SIGINT and ELINT equipment in the following compartments

A – nose radar

D – right chine bay

E – electronics bay

K – left forward mission bay

L – right forward mission bay

M – left forward mission bay

N – right forward mission bay

P – left aft mission bay

Q – right aft mission bay

R – radio equipment bay

S – left aft mission bay

T – right aft mission bay

Variants

SR-71A was the main production variant.

SR-71B was a trainer variant.

SR-71C was a hybrid trainer aircraft composed of the rear fuselage of the first YF-12A (S/N 60-6934) and the forward fuselage from an SR-71 static test unit.

The YF-12 had been wrecked in a 1966 landing accident.

This Blackbird was seemingly not quite straight and had a yaw at supersonic speeds.

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