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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (12): 627023-627023.doi: 10.7527/S1000-6893.2022.27023

• Special Topic of Numerical Simulation of High Speed Vehicles in Near Space • Previous Articles     Next Articles

Influencing factors of active cooling at leading edge of hypersonic vehicles

LUO Shibin, MIAO Zhichao, SONG Jiawen   

  1. School of Aeronautics and Astronautics, Central South University, Changsha 410083, China
  • Received:2022-02-06 Revised:2022-03-07 Published:2022-03-22
  • Supported by:
    Foundation of National Key Laboratory of Science and Technology on Aerodynamic Design and Research(614220121020114); Key R&D Projects of Hunan Province (2021GK2011)

Abstract: The active cooling technology is the key development direction of hypersonic vehicles, and the combination of different active cooling technologies can achieve complementary advantages and provide effective thermal protection for the leading edge of vehicles with high heat flux. This study examines the film-transpiration combined cooling structure on the leading edge of hypersonic vehicles. The CFD numerical calculation model is established to study the influence of angles of attack of 0°, 4°, and 12° on the combined cooling effect, and the combined cooling effect of configurations with different upper wedge angles on the leading edge is analyzed. The results show that the angle of attack increases the temperature difference between the upper and lower halves of the leading edge model. The maximum temperature difference between the upper and lower walls is 639.2 K. The change in the angle of attack affects the flow distribution of the coolant in the structure by influencing the distribution of outside wall pressure. Increasing the upper wedge angle of the leading edge will reduce the distance of the coolant to the downstream of the porous medium. There is an approximate linear growth trend of the outside wall temperature with the increase of the upper wedge angle.

Key words: hypersonic vehicle, film cooling, transpiration cooling, angle of attack, wedge angle of leading edge

CLC Number: