Skip to main content
Article thumbnail
Location of Repository

A new method for predicting the vortex induced aerodynamic characteristics of a body of revolution

By Howard Smith


The problem of mathematically modelling the symmetric vortex pair formed on the lee side of a body of revolution at moderate incidence to the freestream direction is addressed with a view to predicting its aerodynamic characteristics. The objective being to develop a model simple enough to enable rapid calculation whilst maintaining acceptable levels of accuracy. Existing techniques are reviewed and their strengths and weaknesses evaluated. The physics of the flow are explored with an emphasis on its three dimensional aspects. Experimental results, including surface pressure tapping data and flow visualisation, are used to investigate the nature of the flow. To gain a deeper insight into the flow processes less measurable experimentally, Navier-Stokes solutions are examined in considerable detail. The mechanisms of vorticity generation and propagation are explored. A simple mathematical model is presented, based upon an extension to slender body theory, which predicts aerodynamic characteristics that compare well with experiment

Publisher: Cranfield University
Year: 1995
OAI identifier:
Provided by: Cranfield CERES

Suggested articles


  1. (1966). A concept of the Vortex Lift of sharp edge delta wings based on a leading edge suction analogy", doi
  2. (1978). A distributed vortex method for computing the vortex field of a missile. NASA 'IT-1183,
  3. (1911). a Kärmän `Göttinger Nachr, '
  4. (1971). A multivortex method for axisymmetric bodies at angle of attack. doi
  5. (1978). A new approach to roll-up calculations of Soh, W. K. vortex sheets. doi
  6. (1967). A theoretical investigation of the
  7. A theory of the flow past a slender delta doi
  8. (1990). An approximate method for estimating
  9. (1927). and "on the flow of air behind an inclined flat Johansen, F. C plate of infinite span. doi
  10. and An investigation of the normal-force and doi
  11. Attachment and separation in three dimensional flow, section 112-6 of "Laminar boundary layers", Ed. Rosenhead L Oxford
  12. (1922). b Heisenburg 'Phys'.
  13. (1986). Book (Progress in astronautics and (Editors) aeronautics
  14. (1988). Computational Techniques for fluid dynamics, Vol. I& II, doi
  15. (1954). Effect of leading-edge separation on the doi
  16. (1969). Effects of vortex separation on the lift distribution on bodies of elliptic cross section. doi
  17. (1949). Estimation of forces and moments acting on inclined bodies of revolution of high fineness ratio.
  18. Evans Application of Euler and
  19. Extension of the method for predicting
  20. (1955). Flow separation in three dimensions"
  21. (1983). High angle of attack calculations of the subsonic vortex flow on slender bodies. doi
  22. (1966). Hypersonic flow theory. 2nd Edition Probstein, doi
  23. (1966). Improved calculations of leading-edge separation from slender delta wings. doi
  24. (1954). Leading-edge separation from delta wings. doi
  25. (1960). Missile Aerodynamics, doi
  26. Modern developments in fluid dynamics, doi
  27. Modern developments in fluid dynamics.
  28. (1975). Multivortex model of asymmetric shedding on slender bodies at high angle of attack. doi
  29. (1967). Numerical computation of the magnitude and frequency of the lift on a circular cylinder. doi
  30. ogive nose and cylindrical body at high angles of attack", Office National D'etudes et de Recherches Aerospatiales,
  31. (1977). on missiles at high angles of attack. doi
  32. (1985). On the effects of boundary layer transition on a cylindrical afterbody at incidence in low speed flow".
  33. On topological changes of separating flow structures at transition Reynolds numbers", AIAA-87-1266, doi
  34. Peake Topology of two dimensional and three DJ dimensional separated flows, doi
  35. (1981). Predicted vortex shedding from noncircular bodies in supersonic flow. doi
  36. (1985). Prediction of the non-linear aerodynamic Perkins, S. C. characteristics of manoeuvring missiles. doi
  37. (1984). Predictions of the vortex wake for nonPerkins, S. C. circular missiles in supersonic flow.
  38. Pressure and force distributions on an ogive- nosed circular cylinder at high angles of attack in an incompressible airstream", lB 222-83 A 05,27-7-1983, Deutsche Forschungs- und Versuchsanstalt Fur Luft- und Raumfahrt /AVA.
  39. pressure and force measurements on a
  40. (1980). Pressure measurements on an ogivecylinder at high angles of attack with laminar, transitional or turbulent separation". doi
  41. (1974). Separated flow over bodies of revolution Deffenbaugh, using an unsteady discrete-vorticity
  42. (1982). Some effects of boundary layer transition on slender axi-symmetric bodies at incidence in incompressible flow",
  43. (1990). Some trends in missile aerodynamics,
  44. Supersonic conical separation due to shock vorticity, doi
  45. (1977). Symmetric and asymmetric vortices from
  46. (1950). Symmetric vortex separation on circular cylinders and cones. doi
  47. The airflow around a circular cylinder in the region where the boundary layer separate from the surface", doi
  48. (1959). The prediction of separation of the turbulent boundary layer. doi
  49. The structure of the vortex sheet.
  50. (1976). Time development of the flow about an F. D. impulsively started cylinder. doi
  51. (1985). User guide for the SPARV panel program, British Aerospace,
  52. (1955). Vortex interference on slender air planes,
  53. (1979). Vortex shedding from circular doi
  54. (1988). Vortical wakes over a prolate spheroid. doi

To submit an update or takedown request for this paper, please submit an Update/Correction/Removal Request.