Effect of suction on a shock-separated boundary layer - A numerical study
Abstract
The compressible Navier-Stokes 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;
- Navier-Stokes Equation;
- Quantitative Analysis;
- Reynolds Number;
- Fluid Mechanics and Heat Transfer