13.5” Supersonic Wind Tunnel

13.5” Supersonic Wind Tunnel

Wind Tunnel Testing
Thrust Minus Drag Testing
State of the Art Facility
Mach 1 to 4 Range
13.5" Supersonic Wind Tunnel

Channel 2 Supersonic Wind Tunnel

Used to evaluate single stream exhaust system performance using interchangeable nozzle blocks to produce external flow conditions at Mach numbers 1.5, 2, 2.5, 3 and 4. The test section is 13.5 inches in diameter. The exhaust system models are mounted on a 5 inch diameter air supply sting.

For nozzle tests with supersonic external flow (13.5” diameter Test Section.)

  •   External Mach Numbers from 1.5 to 4
  •   Nozzle pressure ratios to 70
  •   Air supply is 450 psig, 10,000 ft3
  •   Ejector system sets tunnel ambient pressure
  •   Axisymmetric plug nozzle blocks with 5 inch diameter sting
  •   Model sting with force balance and flow meter

Find out how we can
support your innovations