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

compressible flows, laminar-turbulent transition, evolution equations of small disturbances, exp(N)-method

Theoretical and applied problems of mechanics