Difficulties associated with nonlinearity of transonic small disturbance equation are avoided by considering linear problem governing rate of change of flow velocity with respect to airfoil thickness ratio parameter and integrating solutions of problem over thickness ratio; solutions for nonlifting airfoils exhibit all commonly observed features of transonic flow; numerical results for sub- and supersonic flow and for flows at Mach number unity are in agreement with other theoretical results and experiment; method could be used to determine airfoil shape for prescribed pressure distribution and to calculate flows with lift.
Solution of transonic airfoil problem through parametric differentiation
AIAA J
AIAA Journal ; 5 , n 3
1967
10 pages
Article (Journal)
English
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