Effect of Wall Suction and Cooling on the Second Mode Instability
Compressible linear viscous stability theory is used to study the effect of combined wall suction and cooling on the second mode instability in a flat plate boundary layer. While wall cooling destabilizes the boundary layer, calculations at Mach 4.5 and 8 show that wall suction may be used to stabilize the boundary layer with respect to second mode (subsonic) instability.
KeywordsBoundary Layer Mach Number Mode Instability Stability Equation Hypersonic Boundary Layer
Unable to display preview. Download preview PDF.
- 1.Lees, L. and Lin, C. C., “Investigation of the Stability of the Laminar Boundary Layer in a Compressible Fluid”, NACA Technical Note No. 1115, 1946 (unpublished).Google Scholar
- 2.Mack, L. M., “Boundary-Layer Stability Theory”, Document No. 900–277, Rev. A, Jet Propulsion Laboratory, Pasadena, CA, 1969.Google Scholar
- 3.Lees, L., “The Stability of the Laminar Boundary Layer in a Compressible Fluid”, NACA Tech. Report No. 876, 1947.Google Scholar
- 4.Malik, M. R., “Prediction and Control of Transition in Hypersonic Boundary Layers”, AIAA 19th Fluid Dynamics, Plasma Dynamics and Lasers Conference, Honolulu, Hawaii, June 8–10, 1987, AIAA Paper No. 87–1414,1987 (unpublished).Google Scholar
- 5.Mack, L. M., “On the Inviscid Acoustic-Mode Instability of Supersonic Shear Flows,”, Fourth Symposium on Numerical and Physical Aspects of Aerodynamic Flows”, California State University, Long Beach, CA, January 16–19, 1989.Google Scholar
- 7.Malik, M. R., “Numerical Methods for Hypersonic Boundary Layer Stability”, HTC Report No. 88–6, June 1988.Google Scholar
- 8.Mack, L. M., “Boundary-Layer Linear Stability Theory”, in Special Course on Stability and Transition of Laminar Flow, AGARD Report No. 709, pp. 3–1 to 3–81, 1984.).Google Scholar