The computation of supersonic flow fields about wing-body combinations by “shock-capturing” finite difference techniques

  • Paul Kutler
  • Harvard Lomax
Session I Fundamental Numerical Techniques
Part of the Lecture Notes in Physics book series (LNP, volume 8)


Shift Condition Delta Wing Finite Difference Technique Shock SHAPE Embed Shock 
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Copyright information

© Springer-Verlag 1971

Authors and Affiliations

  • Paul Kutler
    • 1
  • Harvard Lomax
    • 1
  1. 1.Ames Research Center, NASA Moffett FieldCalif.

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