TY - JOUR
T1 - Studies on the effects of test gas on the flow field around large angle blunt cone flying at hypersonic mach number
AU - Jagadeesh, Gopalan
AU - Nagashetty, Kanderpallt
AU - Reddy, K. P.Jaganntha
AU - Sun, Mingyu
AU - Takayama, Kazuyoshi
N1 - Copyright:
Copyright 2017 Elsevier B.V., All rights reserved.
PY - 2002/11
Y1 - 2002/11
N2 - 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.
AB - 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.
KW - Blunt cones
KW - Hypersonic shock wave
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U2 - 10.2322/tjsass.45.189
DO - 10.2322/tjsass.45.189
M3 - Article
AN - SCOPUS:0036880385
VL - 45
SP - 189
EP - 194
JO - Transactions of the Japan Society for Aeronautical and Space Sciences
JF - Transactions of the Japan Society for Aeronautical and Space Sciences
SN - 0549-3811
IS - 149
ER -