Shock Waves

, Volume 14, Issue 5–6, pp 421–424 | Cite as

Hypersonic flow over a multi-step afterbody

  • V. Menezes
  • S. Kumar
  • K. Maruta
  • K. P. J. Reddy
  • K. Takayama
Technical Note

Abstract

Effect of a multi-step base on the total drag of a missile shaped body was studied in a shock tunnel at a hypersonic Mach number of 5.75. Total drag over the body was measured using a single component accelerometer force balance. Experimental results indicated a reduction of 8% in total drag over the body with a multi-step base in comparison with the base-line (model with a flat base) configuration.The flow fields around the above bodies were simulated using a 2-D axisymmetric Navier–Stokes solver and the simulated results on total drag were compared with the measured results. The simulated flow field pictures give an insight into the involved flow physics.

Keywords

Drag measurement Stepped afterbody Accelerometer balance Hypersonic 

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Copyright information

© Springer-Verlag 2005

Authors and Affiliations

  • V. Menezes
    • 1
  • S. Kumar
    • 2
  • K. Maruta
    • 2
  • K. P. J. Reddy
    • 3
  • K. Takayama
    • 1
  1. 1.Interdisciplinary Shock Wave Research Center, TUBEROTohoku UniversitySendaiJapan
  2. 2.Institute of Fluid ScienceTohoku UniversitySendaiJapan
  3. 3.Department of Aerospace EngineeringIndian Institute of ScienceBangaloreIndia

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