Studies on the effects of test gas on the flow field around large angle blunt cone flying at hypersonic mach number

Gopalan Jagadeesh, Kanderpallt Nagashetty, K. P.Jaganntha Reddy, Mingyu Sun, Kazuyoshi Takayama

Research output: Contribution to journalArticlepeer-review

4 Citations (Scopus)

Abstract

The effect of the test gas on the flow field around a 120° apex angle blunt cone has been investigated in a shock tunnel at a nominal Mach number of 5.75. The shock standoff distance around the blunt cone was measured by an electrical discharge technique using both carbon dioxide and air as test gases. The forebody laminar convective heat transfer to the blunt cone was measured with platinum thin-film sensors in both air and carbon dioxide environments. An increase of 10 to 15% in the measured heat transfer values was observed with carbon dioxide as the test gas in comparison to air. The measured thickness of the shock layer along the stagnation streamline was 3.57 ± 0.17 mm in air and 3.29 ± 0.26 mm in carbon dioxide. The computed thickness of the shock layer for air and carbon dioxide were 3.98 mm and 3.02mm, respectively. The observed increase in the measured heat transfer rates in carbon dioxide compared to air was due to the higher density ratio across the bow shock wave and the reduced shock layer thickness.

Original languageEnglish
Pages (from-to)189-194
Number of pages6
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume45
Issue number149
DOIs
Publication statusPublished - 2002 Nov

Keywords

  • Blunt cones
  • Hypersonic shock wave

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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