A lifting surface theory for the computation of unsteady pressure coefficients on finite wings undergoing harmonic oscill in subsonic, compressible flow
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A panel type mean lifting surface method has been developed for the computation of unsteady pressure distributions on harmonically oscillating wings in compressible, subsonic flow. The velocity potential function has been used as the prime unknown in the formulation. Good agreement is observed between this theory and experiments for finite wings with and without control surfaces in steady and unsteady flow. A novel acceleration potential function based panel method has also been developed which exhibits a simple Kernel function. Limited testing of this method shows good agreement with experiments. This method can perform the desired calculations at approximately four times the speed of the velocity potential formulation. Both methods may be readily extended to include thickness and interference effects.
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Copyright © 1978 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
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- 1978
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