Numerical Solution of Subcritical Flow Past Airfoils
Research and development rept. Jul 1971-Apr 1973
DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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A finite-difference solution technique has been developed for subsonic two-dimensional inviscid flow past lifting airfoils. This work is an adaptation of the method used by Sells 1967. The full governing equations of compressible flow are written in terms of a translated velocity potential which is continuous throughout the flow field. This simplifies solutions for bluff airfoils no Kutta condition where both angle of attack and lift coefficient are specified. The computational plane is the interior of a unit circle obtained by mapping the flow field into the interior of the circle. A line over relaxation matrix method is used for solution of the partial differential equation which in the iteration scheme is coupled with an algebraic equation. The numerical procedure is accurate and well behaved for all subsonic flow conditions.
- Fluid Mechanics