ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW

ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW

An exact theory for non-equilibrium flow past a thin airfoil is given. Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact...

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Bibliographische Detailangaben
1. Verfasser: Ryhming,Inge L
Format: Report
Sprache:eng
Schlagworte:
AIRFOILS
BOUNDARY LAYER
GAS FLOW
GREENS FUNCTIONS
INTEGRAL EQUATIONS
MATHEMATICAL ANALYSIS
PARTIAL DIFFERENTIAL EQUATIONS
SUPERSONIC FLOW
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Zusammenfassung:An exact theory for non-equilibrium flow past a thin airfoil is given. Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact solution. The final expression for the velocity potential shows that the solution is dependent not only on the slope of the airfoil but also on its curvature. As an ex-AMPLE, THE SUPERSONIC FLOW PAST A WEDGE IS CONSIDERED. (Author)