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Relaxation methods for transonic flow about wing-cylinder combinations and lifting swept wings

  • Frank R. Bailey
  • William F. Ballhaus
Conference paper
Part of the Lecture Notes in Physics book series (LNP, volume 19)

Abstract

A mixed elliptic-hyperbolic relaxation method has been applied to the study of a nonlinear small perturbation equation modeling steady, three-dimensional transonic flow. Certain nonlifting wing-body combinations were computed without difficulty, and a numerical procedure for treating lifting wings without bodies was presented. In an effort to simplify the treatment of swept and tapered wings with blunt leading edges, a coordinate transformation has been introduced to map the wing planform into a rectangle. Certain difficulties introduced by this transformation were explored, and results found from its use under valid circumstances were presented and compared with experiment.

Keywords

Vortex Sheet Transonic Flow Sweep Angle Wing Section Supersonic Region 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. Cahill, J. F. and Stanewsky, E., Air Force Flight Dynamics Lab, AFFDL-TR-69-78 (1969).Google Scholar
  2. Klunker, E. B., NASA TN D-6530 (1971).Google Scholar
  3. Krupp, J. A., The Boeing Company, Rep. D180-12958-1 (1971).Google Scholar
  4. Murman, E. M. and Cole, J. D., AIAA J, 9, 114–121 (1971).zbMATHCrossRefADSGoogle Scholar
  5. Saaris, G. R. and Rubbert, P. E., AIAA Paper 72-188 (1972).Google Scholar
  6. Spreiter, J. R. NACA Rep. 1153 (1953).Google Scholar

Copyright information

© Springer-Verlag 1973

Authors and Affiliations

  • Frank R. Bailey
    • 1
  • William F. Ballhaus
    • 2
  1. 1.Ames Research CenterNASAMoffett Field
  2. 2.U. S Army Air Mobility Research and Development LaboratoryMoffett Field

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