Experimental Observations on Film Cooling Effectiveness on Aerodynamic Heating in Hypersonic Flow

被引：0

作者：

Sreekumar, Jithin ^{[1
]}

Vamsi Krishna, Talluri ^{[1
]}

Gupta, Honhar ^{[1
]}

Ibrahim Sugarno, Mohammed ^{[1
]}

机构：

[1] Indian Inst Technol Kanpur, Dept Aerosp Engn, Kanpur 208016, Uttar Pradesh, India

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2024年

关键词：

Aerodynamic Heating; Cooling Technology; Convective Heat Transfer; Heat Flux; Thermal Control and Protection; Thermocouples; Hypersonic Flows; Film Cooling; THERMAL PROTECTION SYSTEM; BLUNT-BODY; REDUCTION; JET; THERMOCOUPLES; NOSE;

D O I：

10.2514/1.A35907

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An experimental campaign was carried out to examine the effectiveness of film cooling on aerodynamic heating at hypersonic velocities. A flat-faced cylindrical model was tested at flow velocity of 2.5 km/s in a hypersonic shock tunnel. The test model was equipped with temperature sensors for convective heat flux measurement. The coolant gas, nitrogen, was injected through a 2 mm orifice housed at the center of the test model at different pressure ratios. Two different flow regimes were observed, steady and unsteady, with the steady flowfield having overall reduction in heat transfer compared to the unsteady one.

引用

页数：8

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