A finite element method for the computation of the transonic flow with shocks past airfoils is presented using the artificial viscosity concept for the local supersonic regime. Generally, the classic element types do not meet the accuracy requirements of advanced numerical aerodynamics requiring special attention to the choice of an appropriate element. A series of computed pressure distributions exhibits the usefulness of the method.
A finite element method for the computation of transonic flow past airfoils
1980-02-01
Report
No indication
English
High-Resolution Finite Volume Computation of Turbulent Transonic Flow Past Airfoils
Online Contents | 1997
|Transonic Flow past Lifting Airfoils
AIAA | 1973
|Two-dimensional transonic flow past airfoils
Engineering Index Backfile | 1951
|Two-dimensional transonic flow past airfoils
TIBKAT | 1951
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