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Supersonic flow computations over aerospace configurations using an Euler marching solverFor fully supersonic flows, an efficient strategy for obtaining numerical solutions is to employ space marching techniques. A full potential marching technique, known as the SIMP code and capable of handling such embedded subsonic regions, has achieved some success analyzing low supersonic Mach number flows. The extension of the full potential approach to the Euler equation which model the exact nonlinear inviscid gas dynamic flow processes is presented. Within the assumption of an inviscid flow, such an Euler marching solver can be applied to a wide class of shocked flows including the hypersonic range. The intent is to maintain some of the basic features of the full potential SIMP code within the Euler solver in dealing with geometry input, gridding techniques, and input/output routines including post processing of results. An Euler marching code known as EMTAC was developed. Results obtained for a variety of configurations involving canard, wing, horizontal tail, flow-through inlet, and fuselage using both the EMTAC and SIMP codes are reported. For shocked cases satisfying the isentropic assumption, the EMTAC and SIMP codes produced practically the same results. In terms of execution time, the EMTAC code is slower.
Document ID
19900000696
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Szema, Kuo-Yen (Rockwell International Science Center Thousand Oaks, CA, United States)
Chakravarthy, Sukumar (Rockwell International Science Center Thousand Oaks, CA, United States)
Shankar, Vijaya (Rockwell International Science Center Thousand Oaks, CA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-4085
NAS 1.26:4085
Accession Number
90N10012
Funding Number(s)
PROJECT: RTOP 505-68-91-02
CONTRACT_GRANT: NAS1-15820
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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