Analysis of generic scramjet external nozzle flowfields employing simulant gasesExperimental and computational results are presented for a generic scramjet nozzle/afterbody model. Mixtures of argon and Freon were employed as simulant scramjet exhaust gases because they correctly model the inviscid simulation parameters of actual scramjet combustion products, allowing test and analysis at significantly reduced temperatures. Air was also employed as an exhaust gas to provide experimental and computational comparisons with simulant gas effects. Several computational aerodynamic analysis codes, employing different levels of theoretical modeling, were applied to compute solutions about the scramjet geometry. The solutions are compared with measured surface static and flowfield pitot pressure data taken in a Mach 6 freestream.
Document ID
19910029844
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tatum, Kenneth E. (Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Monta, William J. (Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Witte, David W. (NASA Langley Research Center Hampton, VA, United States)
Walters, Robert W. (Virginia Polytechnic Institute and State University Blacksburg, United States)