Aeroheating measurement on capsule model with roughness in high-enthalpy shock tunnel HIEST

摘要：

　　An aeroheating measurement test campaign on a capsule model with laminar and turbulent boundary layers was performed in the free-piston shock tunnel JAXA-HIEST.A 250 mm-diameter 6.4%-scale Apollo CM capsule model made of SUS-304 stainless steel was applied in this study.To measure heat flux distribution,the model was equipped with 88 miniature co-axial chromel-constantan thermocouples on its heat shield surface.In order to promote boundary layer transition,a boundary layer trip insert with 13 “pizza box shaped isolated roughness elements,each 1.27 mm square,was placed 17 mm below the models geometric center.Three boundary layer trip inserts with roughness heights of k = 0.3 mm,0.6 mm and 0.8 mm were used to identify the appropriate height to induce transition.Heat flux records with and without roughness elements were obtained for a 28o angle of attack under stagnation enthalpies from H0 = 3.5 MJ/kg to 21 MJ/kg and stagnation pressures from P0 = 14 MPa to 60 MPa.Under these conditions,the Reynolds number based on the model diameter varied from 0.2 to 1.3 million.With roughness elements,the boundary layer became fully turbulent at less than H0 = 9 MJ/kg.However,the boundary layer remained laminar above H0 =13 MJ/kg even with the highest roughness elements.

关键词： Aeroheating Hypersonic Boundary layer transition

作者: Hideyuki Tanno Tomoyuki Komuro Kazuo Sato Kasuhiro Itoh

作者单位: Senior researcher,Japan Aerospace Exploration Agency Kakuda Space Center,Koganesawa,Kimigaya,Kakuda Deputy Manager,Japan Aerospace Exploration Agency Kakuda Space Center,Koganesawa,Kimigaya,Kakuda Miy

会议类型: 国际会议

会议名称: 2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)

会议地点: 上海

会议语种:英文

页码: 1-8

在线出版日期: 2014-09-24（万方平台首次上网日期，不代表论文的发表时间）