Aerothermal boundary layer computation including strong viscous-inviscid flow interaction
Abstract
The present study describes a new 2D compressible, aerothermal boundary layer code. The boundary layer equations associated with the energy equation are solved with an implicit Keller-box scheme. Viscous-inviscid flow coupling is performed by adding an interaction equation which has an elliptic character. The complete system of equations is solved by a multipass procedure. This technique contributes to the stabilization of the method and allows the computation of regions with strong adverse pressure gradients, separation bubbles, and injections in case of film cooling. Comparisons between experimental and theoretical results are provided. Flow characteristics including heat transfer are computed for several cases such as flat plates with strong pressure gradients, and turbine blade boundary layers. Good agreement between computation and experiment is observed, which demonstrates the high accuracy and robustness of the code.
- Publication:
-
ASME, 35th International Gas Turbine and Aeroengine Congress and Exposition
- Pub Date:
- June 1990
- Bibcode:
- 1990gatu.confQ....K
- Keywords:
-
- Boundary Layer Equations;
- Computational Fluid Dynamics;
- Inviscid Flow;
- Thermal Boundary Layer;
- Turbine Blades;
- Viscous Flow;
- Film Cooling;
- Flat Plates;
- Pressure Gradients;
- Robustness (Mathematics);
- Fluid Mechanics and Heat Transfer