Accession Number : AD0434380


Title :   AN EXPERIMENTAL STUDY OF DIFFUSERS IN AN OPENJET, LOW-DENSITY, HYPERSONIC WIND TUNNEL


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Boylan, David E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/434380.pdf


Report Date : Apr 1964


Pagination or Media Count : 70


Abstract : 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.


Descriptors :   *HYPERSONIC DIFFUSERS , DIFFUSERS , HYPERSONIC WIND TUNNELS , PRESSURE , RECOVERY , VISCOSITY


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE