Laminar supersonic flow over a backstep - A numerical solution at higher Reynolds numbersThe Allen-Cheng solution of the flow over a backward facing step is extended to Reynolds numbers up to 16,000 and to inflow boundary-layer height ratios as low as 0.1 by moving the downstream boundary into the recompression region and by smoothing the resulting errors. The boundary conditions in the supersonic outer flow and the downstream boundary conditions in the wake are determined by an extrapolation procedure. Computational results are compared with relevant experimental data. Fair agreement is found between the calculated base pressures and the experimental values, whereas agreement between heat transfer rates appears to be qualitative only.
Document ID
19760052455
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Kronzon, Y. (NASA Ames Research Center Moffett Field, CA, United States)
Rom, J. (Technion - Israel Institute of Technology Haifa, Israel)
Seginer, A. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aerodynamics
Meeting Information
Meeting: Heat Transfer and Fluid Mechanics Institute, Meeting