Advertisement

Flow Field for an Accelerating Axisymmetric Body

  • I. MahomedEmail author
  • H. Roohani
  • B. W. Skews
  • I. M. A. Gledhill
Conference paper

Abstract

This study numerically investigates the compressible flow field near an axisymmetric body that is influenced by constant acceleration at 100 g where the motion is straight and level flight. Selected, instantaneous acceleration and deceleration results are compared to steady-state flow at corresponding projectile Mach numbers. The geometries tested were sharp 10° and 30° half-angle cone-cylinders with constant cylindrical aft section. Significant differences in the behavior of the flow field were found for the transonic Mach number range when compared with steady-state results. This was largely due to relative movement of the shock systems and their influence on the near flow field around the projectile. In particular, acceleration was found to delay the complete development of the bow shock and alter the expansion region at the cone-cylinder interface. Deceleration caused all shock structures to propagate upstream relative to the body and influence the nature of the flow field in a different manner compared to acceleration. The flow history concept was evident in both geometries and is demonstrated using simulation results from acceleration cases.

References

  1. 1.
    G.M. Lilley, R. Westley, A.H. Yates, J.R. Busing, Some aspects of noise from supersonic aircraft. J. R. Aeronaut. Soc. Coll. Aeronaut. Rep. 71, 396–414 (1953)CrossRefGoogle Scholar
  2. 2.
    H. Roohani, B.W. Skews, The influence of acceleration and deceleration on shock wave movement on and around aerofoils in transonic flight. Shock Waves 19, 297–305 (2009)CrossRefGoogle Scholar
  3. 3.
    M.A. Ramaswamy, G. Rajendra, Experimental investigation of transonic flow past a blunt cone-cylinder. J. Spacecr. Rocket. 15(2), 120–123 (1978)CrossRefGoogle Scholar

Copyright information

© Springer International Publishing AG, part of Springer Nature 2019

Authors and Affiliations

  • I. Mahomed
    • 1
    Email author
  • H. Roohani
    • 2
  • B. W. Skews
    • 2
  • I. M. A. Gledhill
    • 2
    • 3
  1. 1.University of the Witwatersrand, Flow Research UnitJohannesburgSouth Africa
  2. 2.Flow Research Unit, School of Mechanical, Industrial and Aeronautical Engineering, University of the WitwatersrandPretoriaSouth Africa
  3. 3.Aeronautic Systems Competence Area, DPSS, CSIRPretoriaSouth Africa

Personalised recommendations