An Equation Splitting Method for Shock Boundary Layer Interaction.
Final rept. 15 Jun 74-31 May 77,
AIRESEARCH MFG CO OF ARIZONA PHOENIX
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An equation splitting numerical method for compressible separated flow is described. The basic equations are developed and solved. Comparison to a laminar shock boundary layer interaction is made. Results show qualitative agreement with discrepancies attributed to detail inaccuracies in the numerical methods. Rapid convergence and low computation times are realized. Author
- Fluid Mechanics