Summary
A numerical method has been developed for calculating the inviscid flow past lifting wing-body combinations by solving a form of the transonic small-perturbation equation for the velocity potential. An outline is given of the formulation of the problem and the procedure for numerical solution. Numerical results are compared with data from wind-tunnel tests on a wing-body configuration, and the variation of body interference with angle of incidence and freestream Mach number is illustrated.
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References
Albone, C.M.; Hall, M.G.; Joyce, M.G.: A method for computing transonic flow about thin lifting swept wings. RAE Technical Report (to be issued).
Albone, C.M.: A finite-difference scheme for computing supercritical flows in arbitrary coordinate systems. RAE Technical Report 74090.
Jameson, A.: Iterative solution of transonic flows over airfoils and wings, including flows at Mach 1. Comm. Pure Appl. Math., 27, 283-309.
Albone, C.M.; Catherall, D.; Hall, M.G.; Joyce, M.G.: An improved numerical method for solving the transonic small-perturbation equation for the flow past a lifting aerofoil. RAE Technical Report 74056.
Albone, C.M.: Further improvements in the solution of the transonic small-perturbation equation for flow past a lifting aerofoil. RAE Technical Report 75101.
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© 1976 Springer-Verlag, Berlin/Heidelberg
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Albone, C.M., Hall, M.G., Joyce, G. (1976). Numerical Solutions for Transonic Flows Past Wing-Body Combinations. In: Oswatitsch, K., Rues, D. (eds) Symposium Transsonicum II. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-81005-3_56
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DOI: https://doi.org/10.1007/978-3-642-81005-3_56
Publisher Name: Springer, Berlin, Heidelberg
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