On computing the location of laminar-turbulent transition in compressible boundary layers

Evolution equations of small disturbances directed to compute the location of laminar-turbulent transition in boundary layers by the $e^N$-method with account of compressibility and heat transfer are described and justified for aerodynamic applications. Results of the 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.