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Design of hypersonic wavecatcher intake at Mach 12 with rectangular-to-elliptical shape transition 被引量:1

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摘要 Wavecatcher(inward-turning)intake flows,at design Mach 12,are investigated numerically,to display the effect of wall temperature on flow structures and intake performance.Hypersonic experiments on shock wave/boundary layer interaction are used to validate the Spalart-Allmaras turbulence model for reproducing the features of hypersonic flow.Simulations of hypersonic intake flow are performed at different wall temperatures,including isothermal T_(w)Z 300 K,T_(w)Z 1000 K,T_(w)Z 2000 K,and the adiabatic case.The shock structures,impinging shock positions,surface streamlines,and the development of internal streamwise vortices are discussed.The mass-averaged performance of intake flow shows that,when the wall temperature changes from T_(w)Z 300 K to adiabatic,the mass capture coefficient decreases from 0.991 to 0.933,the total pressure recovery decreases from 0.200 to 0.083,while exit section Mach number decreases from 4.478 to 3.514.The results suggest that the osculating design method of wavecatcher intake design can successfully be extended to Mach 12,while capturing all airflow at isothermal wall conditions.
出处 《Propulsion and Power Research》 SCIE 2023年第2期167-179,共13页 推进与动力(英文)
基金 the support of the National Natural Science Foundation of China(No.12002261) National Postdoctoral Program for Innovative Talents,China(No.BX20200267) The Young Talent Fund of University Association for Science and Technology in Shaanxi,China(No.20200501) China Postdoctoral Science Foundation(No.2020M673411).
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