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- W132236002 abstract "A method is described for the calculation of two-dimensional unsteady inviscid transonic flow about thin airfoils, including shock waves. This method, a so-called field panel method, is based on the solution of an integral equation which combines a subsonic lifting surface panel method with subsonic source panels in the flow. These source panels account for nonuniformities in the velocity distribution due to airfoil thickness and incidence. For a NACA 6hA006 and for a NACA 6UA010 airfoil transonic results are presented and compared with results of the LTRAN2-NLR code. The good agreement obtained shows the feasibility of the method. The lower computer cost makes this approach attractive for extension to 3-D flows." @default.
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- W132236002 date "1981-09-10" @default.
- W132236002 modified "2023-09-23" @default.
- W132236002 title "A field panel method for the calculation of inviscid transonic flow about thin oscillating airfoils with shocks" @default.
- W132236002 hasPublicationYear "1981" @default.
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