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A comparative study of Navier-Stokes codes for high-speed flowsA comparative study was made with four different codes for solving the compressible Navier-Stokes equations using three different test problems. The first of these cases was hypersonic flow through the P8 inlet, which represents inlet configurations typical of a hypersonic airbreathing vehicle. The free-stream Mach number in this case was 7.4. This 2-D inlet was designed to provide an internal compression ratio of 8. Initial calculations were made using two state-of-the-art finite-volume upwind codes, CFL3D and USA-PG2, as well as NASCRIN, a code which uses the unsplit finite-difference technique of MacCormack. All of these codes used the same algebraic eddy-viscosity turbulence model. In the experiment, the cowl lip was slightly blunted; however, for the computations, a sharp cowl leading edge was used to simplify the construction of the grid. The second test problem was the supersonic (Mach 3.0) flow in a three-dimensional corner formed by the intersection of two wedges with equal wedge angles of 9.48 degrees. The flow in such a corner is representative of the flow in the corners of a scramjet inlet. Calculations were made for both laminar and turbulent flow and compared with experimental data. The three-dimensional versions of the three codes used for the inlet study (CFL3D, USA-PG3, and SCRAMIN, respectively) were used for this case. For the laminar corner flow, a fourth code, LAURA, which also uses recently-developed upwind technology, was also utilized. The final test case is the two-dimensional hypersonic flow over a compression ramp. The flow is laminar with a free-stream Mach number of 14.1. In the experiment, the ramp angle was varied to change the strength of the ramp shock and the extent of the viscous-inviscid interaction. Calculations were made for the 24-degree ramp configuration which produces a large separated-flow region that extends upstream of the corner.
Document ID
19910001556
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rudy, David H. (NASA Langley Research Center Hampton, VA, United States)
Thomas, James L. (NASA Langley Research Center Hampton, VA, United States)
Kumar, Ajay (NASA Langley Research Center Hampton, VA, United States)
Gnoffo, Peter A. (NASA Langley Research Center Hampton, VA, United States)
Chakravarthy, Sukumar R. (Rockwell International Science Center Thousand Oaks, CA., United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1989
Publication Information
Publication: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12
Subject Category
Aerodynamics
Accession Number
91N10869
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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