Abstract
This work investigates the effect of two-dimensional surface deformations on hypersonic boundary-layer stability. The deformations are obtained from previous research and represent the characteristic response of integrated thermal protection system panels due to combined aerodynamic and thermal loading. Boundary-layer stability is assessed using linear stability theory and the parabolized stability equations for several different cases, such as deformation direction, deformation location, multiple deformations in series, structural boundary condition, surface temperature, the combined effect of Mach number and altitude, and deformation-mode shape. The broad set of results provides important insight into the conditions where thermomechanical compliance can promote, or even possibly delay, hypersonic boundary-layer transition.
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