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AFE base flow computationsHypersonic wake flows behind the Aeroassist Flight Experiment (AFE) geometry are analyzed using two Navier-Stokes flow solvers. Many of the AFE wake features observed in ballistic-range shadowgraphs are simulated using a simple, two-dimensional semicylinder geometry at moderate angles of attack. At free-stream conditions corresponding to a Hypersonic Free Flight Facility (HFFF) AFE experiment, the three-dimensional base flow for the AFE geometry is computed using an ideal-gas, Navier-Stokes solver. The computed results agree reasonably well with the shadowgraphs taken at the HFFF. An ideal-gas and a nonequilibrium Navier-Stokes solver have been coupled and applied to the complete flow around the AFE vehicle at the free-stream conditions corresponding to a nomial trajectory point. Limitations of the coupled ideal-gas and nonequilibrium solution are discussed. The nonequilibrium base flow solution is analyzed for the wake radiation and the radiation profiles along various lines of sight are compared. Finally, the wake unsteadiness is predicted using experimental correlations and the numerical solutions. An adaptive grid code, SAGE, has been used in all the simulations to enhance the solution accuracy. The grid adaptation is found to be necessary in obtaining base flow solutions with accurate flow features.
Document ID
19910058815
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Venkatapathy, Ethiraj
(Eloret Corp. Palo Alto, CA, United States)
Prabhu, Dinesh K.
(Eloret Institute Palo Alto, CA, United States)
Palmer, Grant
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-1372
Accession Number
91A43438
Funding Number(s)
CONTRACT_GRANT: NCC2-653
CONTRACT_GRANT: NCC2-420
Distribution Limits
Public
Copyright
Other

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