Effect of suction on a shockseparated boundary layer  A numerical study
Abstract
The compressible NavierStokes equations are solved numerically in order to study boundary layer control through suction. Two test cases are used to establish the accuracy and reliability of the present code: (1) freestream Mach number of 2.0, shock angle of 31.347 deg, and Reynolds number of 0.284 x 10 to the 6th based on the distance of the shock from the leading edge; and (2) freestream Mach number of 2.0, shock angle of 32.585 deg, and Reynolds number of 0.296 x 10 to the 6th. The computations make possible a quantitative prediction of the suction effect.
 Publication:

AIAA Journal
 Pub Date:
 November 1979
 DOI:
 10.2514/3.7624
 Bibcode:
 1979AIAAJ..17.1268T
 Keywords:

 Boundary Layer Separation;
 Numerical Analysis;
 Shock Wave Interaction;
 Suction;
 Free Flow;
 Mach Number;
 NavierStokes Equation;
 Quantitative Analysis;
 Reynolds Number;
 Fluid Mechanics and Heat Transfer