AEDC User Test Facilities
(Nominal Values)
Hypersonics/Aerodynamics

  Test Section Size, in. Total Pressure, psia Total Temperature, R Speed Range Pressure Altitude, ft Dynamic Pressure, psf Reynolds No./ft (x106) Primary Use
Supersonic Wind Tunnel A 40 x 40 1.5 to 200 530 to 750 Mach 1.5 to 5.5 16,000 to 151,000 53 to 1,780 0.3 to 9.2 (6) (7) (14)
Hypersonic Wind Tunnel B 50 diam 20 to 900 700 to 1,350 Mach 6 to 8 98,000 to 180,000 43 to 590 0.3 to 4.7 (6) (7) (14)
Hypersonic Wind Tunnel C 50 diam 200 to 1,900 1,650 to 1,950 Mach 10 132,000 to 188,000 43 to 430 0.3 to 2.4 (6) (7) (14)
Aerothermal Wind Tunnel C 25 diam Free Jet 200 to 2,000 1,220 to 1,900 Mach 8 95,000 to 149,000 132 to 1,322 0.7 to 7.8 (6) (7) (13)
25 diam Free Jet 20 to 180 720 to 1,660 Mach 4 56,000 to 105,000 231 to 1,928 0.2 to 8.1 (6) (7) (13)
Aerodynamic and Propulsion Test Unit (APTU) 32 diam 20 to 160 700 to 1,000 Mach 2.20 Sea Level to 40,000 900 to 7,300 3.15 (1) (3) (4) (6) (7) (9) (11) (12) (13)
36 diam 20 to 300 700 to 1,200 Mach 2.72 10,000 to 70,000 600 to 9,300 3.16
  40 to 300 700 to 1,300 Mach 3.50 35,000 to 75,000 650 to 4,800 1.10
  20 to 240 700 to 1,150 Mach 2.55 Sea Level to 65,000 700 to 8,500 2.17
42 diam Free Jet 50 to 300 700 to 1,600 Mach 4.10 55,000 to 80,000 500 to 2,900 1.6
Hypervelocity Range/Track G 120 diam - - - - - - To 24,000 fps Sea Level to 244,000 - - - - - - (8)
Hypervelocity Impact Range S1 Target Tank 30 diam - - - - - - To 28,000 fps Sea Level to 105 torr - - - - - - (10)

Use Legend:

(1) Rockets
(2) Turbojets
(3) Ramjets
(4) Missile Base Heating Models
(5) Space Environmental Tests
(6) Aerodynamic Models
(7) Aerothermodynamic Models
(8) Aeroballistic Models
(9) Combined Aerodynamic Inlet and Propulsion System Tests
(10) Impact Studies
(11) Free-Jet Expansion of Rocket Exhaust Plumes
(12) Ablative Materials
(13) Ablative and Erosive Materials
(14) Store/Stage/Separation