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Study of shock formation around various wing shapes in supersonic flow using colour schlieren method

  • Unique Paper ID: 148503
  • Volume: 6
  • Issue: 2
  • PageNo: 224-227
  • Abstract:
  • Summary of the project is to be finding the effects of different wing shapes and size in supersonic flight. The wing shapes include delta, double delta and other some shapes. By using schlieren method and BOS method in softwares Ansys and designed in Catia. Using common fuselage size and shape according to blockage ratio of supersonic wind tunnel test section and various wing shapes.
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  • ISSN: 2349-6002
  • Volume: 6
  • Issue: 2
  • PageNo: 224-227

Study of shock formation around various wing shapes in supersonic flow using colour schlieren method

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