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A Theoretical Study of Body Drag in Subcritical Axisymmetric Flow

  • D F Myring (a1)

A method of predicting body drag in subcritical axisymmetric flow is outlined which requires only detailed body shape, free-stream conditions and transition point to be prescribed. Results of calculations for a range of body shapes are shown essentially to confirm information in Royal Aeronautical Society Data Sheets but clearly demonstrate that fineness ratio alone is not sufficient to characterise body shape. For example, at a fixed fineness ratio of 0.18, detailed changes in body contour are shown to produce 10 per cent changes in drag coefficient.

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1 Young, A D Royal Aeronautical Society Aerodynamics Data Sheets. Engineering Sciences Data Unit.
2 Young, A D The calculation of the total and skin-friction drags of bodies of revolution at zero incidence. R&M 1874, 1939.
3 Myring, D F The profile drag of bodies of revolution in subsonic axisymmetric flow. RAE TR 72 234, 1972.
4 Hess, J L Smith, A M O Calculation of potential flow about arbitrary bodies. Progress in Aeronautical Sciences, Vol 8, Pergamon, 1967.
5 Luxton, R E Young, A D Generalised methods for the calculation of the laminar compressible boundarylayer characteristics with heat transfer and non-uniform pressure distribution. R&M 3233, 1962.
6 Head, M R Entrainment in the turbulent boundary layer. R&M 3152, 1960.
7 Myring, D F The interaction of a turbulent boundary layer and a shock at hypersonic Mach numbers. AGARD Conference Proceedings 30, 1968.
8 Coles, D The law of the wake in the turbulent boundary layer. Journal of Fluid Mechanics,Vol 1, p 191, 1956.
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The Aeronautical Journal
  • ISSN: 0001-9259
  • EISSN: 2398-2179
  • URL: /core/journals/aeronautical-journal
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