## Abstract

At transonic speeds, shock waves appear in flowfields about aircraft wings, in turbomachinery blade passages, and in air-breathing-engine inlets and diffusers. The interactions of these shock waves with turbulent boundary layers on the solid surfaces result in complex flow phenomena. In this paper, we study the shock/boundary-layer interaction flows by numerically solving the mass-averaged compressible thin-layer Navier-Stokes equations in conjunction with a zero-equation Baldwin-Lomax and a two-equation k- epsilon turbulence model. The numerical procedure is based on a finite-volume Runge-Kutta time-stepping scheme which is stable for Courant numbers less than 2 ROOT 2. The spatial terms are central differenced, and a combination of second- and fourth-order artificial dissipation is added to stabilize the algorithm. The algorithm also employs enthalpy damping and variable time steps to speed convergence to steady state. The flowfields due to shock/boundary-layer interaction on a flat plate, in a compression corner, and on an airfoil are calculated. Numerical results are compared with calculations of other investigators, asymptotic theory, and experimental data.

Original language | English |
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State | Published - 1985 |