Measurement of Temperature Field Around Spiked Bodies at Hypersonic Mach Numbers
An investigation of a high enthalpy hypersonic flow has been made over an axisymmetric spiked body at a Mach number of 10.06. Temperature being one of the important physical quantities in hypersonic flows over such variable drag devices, this work aims at characterizing temperature in the shock layer for one such body. A flat-faced cylinder, with a diameter of 70 mm, and a conical nose spike of length 70 mm, screwed into it, were used for the experiments at zero angle of incidence. A well-established technique, the two-color ratio pyrometry (TCRP), has been used for temperature characterization using a DSLR camera. The results were in good agreement with the temperature predicted in the stagnation region by the STN (shock tube and nozzle calculations for equilibrium air) code.
The authors are grateful to Defence Research and Development Organization (DRDO), India, for their financial support in carrying out this work. Thanks also to Jeevan, Murthy, Kumar, Rajagopal, and Raghu Narayan for their contribution. Colleagues, namely, Tarandeep Singh, Dr. Mohammed Ibrahim. S and Abhishek Khatta are greatly acknowledged for their invaluable help in performing the experiments.
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