Abstract
Abstract Evolution equations of small disturbances aimed to compute the location of a laminar–turbulent transition in boundary layers by the e N -method taking into account the compressibility and heat transfer are described and justified for aerodynamic applications. The results of computation of N-factors and transition locations with the use of locally-parallel flow assumption for a flat plate exposed to supersonic flow at zero angle of attack are given. The results agree well with known numerical and experimental data.
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