Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

Wang Xiaopeng; Zhang Chen'an; Zhai Jian; Wang Famin; Ye Zhengyin

doi:10.11729/syltlx20190080

Volume 33 Issue 4

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Journal of Experiments in Fluid Mechanics > 2019 > 33(4): 52-57. > DOI: 10.11729/syltlx20190080

Wang Xiaopeng, Zhang Chen'an, Zhai Jian, Wang Famin, Ye Zhengyin. Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(4): 52-57. DOI: 10.11729/syltlx20190080

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Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

1.
National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China
2.
State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

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Received Date: June 23, 2019
Revised Date: July 16, 2019

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Abstract

Long-range aerodynamic heating is a key scientific problem. In this paper, the cone-derived waverider is designed firstly and then the characteristics of the heat flux distribution along the leading edge and on the lower surface of the waverider are studied by means of the high enthalpy wind tunnel test and the high temperature chemical non-equilibrium aerodynamic heating numerical calculation. Results show that:The high heat flux mainly concentrates on the small region around the stagnation point and the change of angle of attack (0°~6°) does not have an obvious effect on the high heat flux region at the leading edge, but it induces a significant increase of the heat flux on the lower surface. In addition, the change of the sideslip angle (0°~4°) has a significant effect on the heat flux at the leading edge, so it is not recommended to fly with a large sideslip angle.
- waverider,
- real gas effect,
- aero-heating,
- high enthalpy wind-tunnel test,
- numeri-cal simulation

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