Supersonic Boundary Layer Stability over a Rough Wall.
Final rept. 1 Aug 80-30 Sep 84,
MONTANA STATE UNIV BOZEMAN DEPT OF MECHANICAL ENGINEERING
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Measurements of the growth or damping of natural disturbances in a laminar boundary layer at Mach 3 have been made. Unit Reynolds number and roughness effects have been documented. A primary mode, three dimensional unstable region was identified which has a minimum critical Reynolds number of 180. Amplification rates within this region agree well with theory except that show higher amplification than expected. A second unstable region was discovered between this region and the transition onset defined by the first departure from laminar similarity. Much higher frequencies and amplification rates are found in this region. Increasing unit Reynolds number decreases overall amplification rates and increases transition distance. Random roughness was found to unsuitable for stability studies. Keywords Supersonic flow.
- Fluid Mechanics