+ Visit NASA.gov + Contact NASA   + Home Collection > NASA  Author > Mekkes, Gregory L.  NASA Center > Langley Research Center  Publication Year > 1991-2000 > 1993  Subject > A-C > Aerodynamics  Availability Options > Order From Other Sources  Item/Media Type > Preprint  Item/Media Type > NASA Report > Special Publication (SP)  Note: Start a new navigation search by selecting a link above     Previous Record | Next Record + Back to Results   + Printer Friendly Title: Computational analysis of hypersonic shock wave/wall jet interaction Author(s): Mekkes, Gregory L. Abstract: The purpose of this study is to investigate the CFD code General Aerodynamic Simulation Program (GASP) for application to a specific scramjet combustor phenomenon, that of an adverse pressure gradient caused by an oblique shock wave impinging upon a wall cooling film. The basis of this investigation is data available from an existing experimental study, which includes wall pressure, wall heat transfer, and schlieren photographs. This experimental study was conducted at a nominal Mach number of 6.0 in the Calspan 48-inch shock tunnel. The particular case of interest generates flow separation at the shock impingement point. Two algebraic turbulence models, the Baldwin-Lomax model and the Goldberg model, are considered for this computational study. Resultant computational wall pressure and heat transfer for both turbulence models are compared with experimental data. The Goldberg turbulence model provides a more accurate prediction of the recirculation region, and as a result, a better comparison with the experimental data. NASA Center: Langley Research Center Publication Date: Jan 1, 1993 Document Source: Other Sources No Digital Version Available: Go to Tips On Ordering Document ID: 19930037116 Accession ID: 93A21113 Publication Information: 13 p., Number of Pages = 13 Report Number: AIAA PAPER 93-0604 Contract-Grant-Task Number: NAS1-19320 Meeting Information: AIAA, Aerospace Sciences Meeting and Exhibit, 31st, Jan. 11-14, 1993, Reno, NV, United States Keywords: COMBUSTION CHAMBERS; COMPUTATIONAL FLUID DYNAMICS; FILM COOLING; SHOCK WAVE INTERACTION; WALL JETS; FUEL INJECTION; HYPERSONIC FLOW; OBLIQUE SHOCK WAVES; SHOCK TUNNELS; TURBULENCE MODELS; Notes: AIAA, Aerospace Sciences Meeting and Exhibit, 31st, Reno, NV, Jan. 11-14, 1993 Accessibility: Unclassified; Copyright; Unlimited; Publicly available; Updated/Added to NTRS: 2004-11-03 + Back to Top + Sponsored by the NASA Scientific and Technical    Information Program + 2004 Vision for Space Exploration + Freedom of Information Act + NASA Web Privacy Policy and Important Notices + NASA Disclaimers, Copyright Notice,    and Terms and Conditions of Use NASA Official: Calvin Mackey Page Curator: NASA Center for AeroSpace Information (help@sti.nasa.gov) Last Updated: July 5, 2007