Stability Analysis of the Compressible, Adiabatic Similar Boundary Layer Equations (Lower Branch).
Final rept. May-Aug 80,
AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
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In a previous report the authors analyzed the stability of the lower branch solutions of the incompressible M sub infinity O Falkner-Skan boundary layers. There a perturbation analysis to these boundary layers was performed resulting in the Rayleigh stability equation. Eigen value solutions were obtained for the Rayleigh equation for different adverse pressure gradient beta values. All retarded flows were found to be unstable for a small range of frequencies with the amplification factor increasing as the extent of reversed flow increased. In this report they have entended that work by including the effect of Mach number M sub infinity on the stability of adiabatic S sub W O Falker-Skan equations for beta -.04, -.08, -.12, -.16 and -.19884. We found out that in all these cases as the Mach number M sub infinity increases the instability of flow decreases. In most of the cases the instability almost completely disappeared at M sub infinity 3.
- Numerical Mathematics
- Fluid Mechanics