A thorough experimental investigation of shock/shock interferences in high Mach number flows |
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| Institution: | 1. Central Aerohydrodynamics Institute (TsAGI), Zhukovsky, 140180 Russia;2. Office National d''Etudes et de Recherches Aérospatiales (ONERA), 92320 Châtillon cedex, France;1. School of Aeronautics, Northwestern Polytechnical University, Xi''an, Shaanxi, 710072, PR China;2. School of Astronautics, Northwestern Polytechnical University, Xi''an, Shaanxi, 710072, PR China;1. Dip. di Ingegneria Meccanica e Aerospaziale, Università di Roma “La Sapienza”, Via Eudossiana 18, 00184 Rome, Italy;2. Scuola di Ingeneria – Università degli Studi della Basilicata, Viale dell''Ateneo Lucano 10, 85100 Potenza, Italy;1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing, 100081, China;2. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China;3. School of Engineering Sciences, University of Chinese Academy of Sciences, Beijing, 100049, China;1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;2. College of Aerospace Engineering, Chongqing University, Chongqing 400044, China;3. State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, CAS, Beijing 100190, China |
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| Abstract: | The Types III and IV interference flows, as defined by Edney, and corresponding heat transfer distributions were investigated experimentally. The model consists of a cylindrically blunted plate and a wedge serving as an oblique shock generator. The ‘thin wall’ technique was used for heat transfer measurements on the cylinder surface. These experiments were carried out in the TsAGI short duration wind tunnel UT-1 at Mach numbers 6 and 16 in air and at Mach number 6.6 in carbon dioxide. The Reynolds number based on the plate bluntness diameter was varied in the range 2.2×104 to 1.6×106. Tests of the cylinder alone (without the wedge) at Mach number 6 and for different Reynolds numbers revealed an influence of incoming disturbances on the stagnation line heat transfer. The influence of the impinging shock location on the interference heat transfer was carefully investigated. Systematic calculations of inviscid flow at Mach number 6 were also performed. Estimations of the maximum interference heat transfer rate, based on these calculations and a boundary layer approach, compare well with the data. Influence of the specific heat ratio on the interference flow was studied. These experiments and calculations revealed important features of interference flow patterns and heat transfer distributions. |
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