TESTING THE FUTURE

13.5” Supersonic Wind Tunnel

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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.

Installed Propulsion Tests

Channel 2 can be used to determine nozzle system thrust and discharge coefficients with supersonic external flow. Shock waves in the flow can be observed for correlation with CFD.

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Installed Propulsion Tests for 13.5" Supersonic Wind Tunnel

Mach 1 to 4 Range

Freestream Mach number is generated by interchangeable annular nozzle throats mounted on the sting upstream of the model.

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13.5" Supersonic Wind Tunnel with Mach 1 to 4 Range

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

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