Lifting Surface Theory for Wings of Arbitrary Planform
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This theory permits the calculation of pressure distributions over a thin airfoil in steady, inviscid, incompressible flow or given a desired chordwise pressure distribution the camber line of an ideal wing can be determined. The method treats the circulation about the wing as a continuous vortex sheet of variable strength covering the wing planform and trailing downstream to infinity. The results of the present numerical solution for the pressure distribution solution are not conclusive. However the solution for the camber line of an ideal wing is in reasonable agreement with published two dimensional results.
- Fluid Mechanics