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Numerical Solutions for Transonic Flows Past Wing-Body Combinations

  • C. M. Albone
  • M. G. Hall
  • Gaynor Joyce
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

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.

Keywords

Mach Number Transonic Flow Inviscid Flow Lower Mach Number Freestream Mach Number 
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References

  1. 1.
    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).Google Scholar
  2. 2.
    Albone, C.M.: A finite-difference scheme for computing supercritical flows in arbitrary coordinate systems. RAE Technical Report 74090.Google Scholar
  3. 3.
    Jameson, A.: Iterative solution of transonic flows over airfoils and wings, including flows at Mach 1. Comm. Pure Appl. Math., 27, 283-309.Google Scholar
  4. 4.
    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.Google Scholar
  5. 5.
    Albone, C.M.: Further improvements in the solution of the transonic small-perturbation equation for flow past a lifting aerofoil. RAE Technical Report 75101.Google Scholar

Copyright information

© Springer-Verlag, Berlin/Heidelberg 1976

Authors and Affiliations

  • C. M. Albone
    • 1
  • M. G. Hall
    • 1
  • Gaynor Joyce
    • 1
  1. 1.Royal Aircraft EstablishmentFarnboroughHampshireEngland

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