Abstract
Linear stability theory is used to determine the effect of transverse curvature on the estimated location of the onset of transition for supersonic boundary layers. Results have been obtained for Mach 5 and Mach 1.25 boundary layers formed over cylinders and sharp cones. As transverse curvature increases, the growth rates for the first mode (asymmetric) instability increase, whereas those for the second mode decrease. The overall effect of increasing curvature is to lower the transition Reynolds number at the Mach numbers studied
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