Transient analysis of counterflowing jet over highly blunt cone in hypersonic flow |
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| Institution: | 1. Department of Mechanical Engineering, Iran University of Science & Technology, Narmak, Tehran 16846, Iran;2. Faculty of Mechanical Engineering, Babol University of Technology, Babol, Iran;1. General Control Department, OneSpace Science and Technology CO. Ltd., Beijing 100080, China;2. China Academy of Launch Vehicle Technology, Beijing 100076, China;3. Department of Mechanical Engineering, University of Sheffield, Sheffield S1 3JD, UK;4. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan 410073, China;5. Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang, Sichuan 621000, China;6. Department of Mechanical & Aerospace Engineering, University of Strathclyde, Glasgow G1 1XJ, UK;1. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China;2. Hypervelocity Aerodynamics Institute, Chinese Aerodynamics Research and Development Center, Mianyang 621000, People’s Republic of China;3. Department of Chemical Engineering, School of Engineering & Applied Science, Khazar University, Baku, Azerbaijan;1. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan 410073, People''s Republic of China;2. Department of Chemical Engineering, School of Engineering & Applied Science, Khazar University, Baku, Azerbaijan |
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| Abstract: | Understanding the characteristics of various Counterflowing jets exiting from a nose cone is crucial for determining heat load reduction and usage of this device in various conditions. Such jets can undergo several flow regimes during venting, from initial supersonic flow, to transonic, to subsonic flow regimes as the pressure of jet decreases. A bow shock wave is a characteristic flow structure during the initial stage of the jet development, and this paper focuses on the development of the bow shock wave and the jet structure behind it. The transient behavior of a sonic counterflow jet is investigated using unsteady, axisymmetric Navier–Stokes solved with SST turbulence model at free stream Mach number of 5.75. The coolant gas (Carbon Dioxide and Helium) is chosen to inject into the hypersonic air flow at the nose of the model. The gases are considered to be ideal, and the computational domain is axisymmetric. The jet structure, including the shock wave and flow separation due to an adverse pressure gradient at the nose is investigated with a focus on the differences between high diffusivity coolant jet (Helium) and low diffusivity coolant jet (CO2) flow scenarios. |
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