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Country Flag

Lockheed

SR-71 Blackbird

RECONNAISSANCE


Family:
SR-71
Type:
Turbojet aircraft

Origin:
Country FlagUnited States
Manufacturer:
1964-1999

Updated March 8, 2024
Aircraft picture
SR-71 - NASA. CC-BY-SA-2.0

General characteristics (5)

  • Role
    Reconnaissance
  • Wing
    Fixed wing
  • Crew
    2
  • Engine count
    2
  • ICAO type designator
    SR71

Structural data (9)

  • Wingspan
    55 ft 7 in (16.94 m)
  • Length
    107 ft 5 in (32.74 m)
  • Height
    18 ft 6 in (5.64 m)
  • Wingspan
    55 ft 7 in (16.94 m)
  • Aspect ratio
    1.7
  • Wing area
    1,800 sq ft (170 m2)
  • Wheel track
    16 ft 8 in (5 m)
  • Wheelbase
    37 ft 10 in (12 m)
  • Wing loading
    84 lb/sq ft (410 kg/m2)

Performance (5)

  • Ferry range
    2,824 nmi (3,250 mi, 5,230 km)
  • Fuel capacity
    12,219.2 US gal (46,255 L) in 6 tank groups (9 tanks)
  • Rate of climb
    11,820 ft/min (60.0 m/s)
  • Service ceiling
    85,000 ft (26,000 m)
  • Thrust-to-weight ratio
    0.44

Speeds (2)

  • Maximum
    1,910 kn (2,200 mph, 3,540 km/h) at 80,000 ft (24,000 m)
  • Maximum Mach
    Mach 3.3

Weights (3)

  • MTOW
    172,000 lb (78,018 kg)
  • Gross
    152,000 lb (68,946 kg)
  • Empty
    67,500 lb (30,617 kg)

Engine options (1)

Option 1:

  • Model
    J58
  • Manufacturer
    Country FlagPratt & Whitney
  • Type
    Turbojet
  • Length
    180 in (4,600 mm) (an additional 6 in (150 mm) at max. temp.)
  • Diameter
    50 in (1,300 mm)
  • Dry weight
    approx. 6,000 lb (2,700 kg)
  • Compressor
    9-stage, axial flow
  • Combustors
    cannular 8 burner cans in an annular combustion casing
  • Turbine
    two-stage axial flow
  • Fuel type
    JP-7, JP-4 or JP-5 for emergency refuelling from any tanker (Mach 1.5 limit)
  • Oil system
    pressure spray return system with fuel-cooled oil cooler
  • Maximum thrust (ISA SL)
    Installed 113.43 kN wet, 80.07 kN dry. Uninstalled 151.24 kN wet, 111.21 kN dry
  • Pressure ratio
    8.8 at take off
  • Bypass ratio
    zero up to Mach 2, rising to 0.25 to afterburner above Mach 3
  • Air mass flow
    300 lb/s (8,200 kg/min) at take-off power
  • SFC
    1.9 lb/(lbfh) or 54 g/(kNs)
  • Thrust-to-weight ratio
    5.23

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