Hypersonic flow over a multi-step afterbody

V. Menezes, K. Takayama, S. Kumar, K. Maruta, K. P.J. Reddy

Research output: Contribution to journalArticlepeer-review

16 Citations (Scopus)

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.

Original languageEnglish
Pages (from-to)421-424
Number of pages4
JournalShock Waves
Volume14
Issue number5-6
DOIs
Publication statusPublished - 2005 Dec 1

Keywords

  • Accelerometer balance
  • Drag measurement
  • Hypersonic
  • Stepped afterbody

ASJC Scopus subject areas

  • Mechanical Engineering
  • Physics and Astronomy(all)

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