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- W2022235246 abstract "The “inverse” or “design” problem in aerodynamics, which solves for the airfoil shape that induces a prescribed chordwise surface pressure subject to additional requirements on trailing edge closure, is considered in the transonic small-disturbance limit. A new formulation for the stream function ψ is suggested which uses well-set Neumann conditions on the chordwise slit, with the degree of closure dictated by a specified jump in ψ across the downstream slit emanating from the trailing edge. The boundary-value problem is solved by a type-dependent relaxation method that automatically generates closed airfoils on convergence. Computed airfoil shapes using subcritical and supercritical pressure distributions obtained from existing finite-difference analysis codes, in the latter case, with and without shockwaves, give results in reasonable agreement with the original specified shapes, and validate the basic ideas." @default.
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- W2022235246 date "1979-12-01" @default.
- W2022235246 modified "2023-10-10" @default.
- W2022235246 title "Airfoil Design in Subcritical and Supercritical Flows" @default.
- W2022235246 doi "https://doi.org/10.1115/1.3424650" @default.
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