AN EXPERIMENTAL STUDY OF DIFFUSERS IN AN OPENJET, LOW-DENSITY, HYPERSONIC WIND TUNNEL
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An experimental investigation of supersonic diffuser performance in a flow regime in which viscous and compressibility influences are equally important was conducted. The investigation involved Mach numbers from 6 to 16. 5. It is shown that, although diffuser recovery compared to higher density regimes is small, using the proper diffuser allowed the required wind tunnel exhaust pressure to be up to 35 times the pressure existing in the test chamber. While this may not seem exceptional at first glance, it is important to note that this was achieved in conjunction with Reynolds numbers on the order of 10 to the minus 3 power below those typical of tunnels yielding higher recoveries.
- Fluid Mechanics