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Effect of Cooling on Boundary-Layer Stability at Mach Number 3

Effect of Cooling on Boundary-Layer Stability at Mach Number 3

Mack, L.
URI: http://hdl.handle.net/2014/36709
Date: 1992
Citation: N/A

Abstract:

This paper describes the calculation of the effect of wall cooling on the instability of a two-dimensional, flat-plate supersonic boundary layer under stratospheric flight conditions at Mach 3 using both the inviscid and viscous linear stability theories.

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