Author:
Chuvakhov P. V.,Egorov I. V.
Abstract
Abstract—
The linear and nonlinear stages of disturbance development in the supersonic boundary layer over a 10° expansion corner is investigated numerically within the framework of Navier—Stokes equations for Mach number 3. The effect of sudden flow expansion on the disturbance evolution is analyzed. The flow stabilization effect observable in the aerodynamic experiment is also discussed.
Subject
Fluid Flow and Transfer Processes,General Physics and Astronomy,Mechanical Engineering
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