A MACH 6 External Nozzle Experiment with Argon-Freon Exhaust Simulation

Paper #:
  • 892315

Published:
  • 1989-09-01
Citation:
Pittman, J., "A MACH 6 External Nozzle Experiment with Argon-Freon Exhaust Simulation," SAE Technical Paper 892315, 1989, https://doi.org/10.4271/892315.
Pages:
12
Abstract:
A scramjet exhaust simulation technique for hypersonic wind tunnel testing has been developed. Mixtures of Argon and Freon correctly match the inviscid simulation parameters of Mach number, static-pressure ratio, and the ratio of specific heats at the combustor exit location; this simulation is accomplished at significantly reduced temperatures and without combustion. An investigation of nozzle parametrics in a Mach 6 freestream showed that the external nozzle ramp angle, the cowl trailing-edge angle, an external nozzle flow fence and the nozzle static-pressure ratio significantly affected the external nozzle thrust and pitching moment as measured by the integration of surface-pressure data. A comparison of Argon-Freon and air exhaust simulation showed that the external nozzle thrust and pitching moment were in error by roughly a factor of 2 using air due to the incorrect match of the ratio of specific heats. An assessment of two-dimensional Euler and Navier-Stokes codes for predicting external nozzle aerodynamic characteristics was made by comparing computed and experimental results.
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