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<p>The objective of this thesis was to contribute to the development of a second-order approximation to the steady and oscillatory lifting flow past low aspect ratio wings by establishing the validity of a NASA-Ames developed incompressible three-dimensional flow panel code named PMARC, which would subsequently be used to test the range of validity of this second-order theory. The steady state configurations modelled in the validation process include swept back, delta and rectangular wings, an F5 wing and three equivalent bodies of revolution. Oscillatory cases were also run with one delta and the F5 wings and their respective equivalent bodies of revolution, as well as with one spindle. In steady state, comparison with experimental and theoretical data proved PMARC to be very accurate for lift and pressure calculations, but revealed a discrepancy in the velocity distribution calculation around delta wings. This finding was corroborated by applying the slender body/slender wing theory (Oswatitsch-Keune theory) to the delta wing. The unsteady state results are presented, but their validation is left for future work. As part of its primary objective, this thesis also presents a computer code that generates the F5 wing equivalent body of revolution from its chordwise section definition. In order to be used as base software to the second-order theory, PMARC will have to be corrected, or a new software will have to be validated.
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Carrier, Alain</div>
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