Experiments were carried out in hypersonic shock tunnel in Defence Research and Directorate Laboratory at hypersonic Mach number of 7.25 using an 11.37° apex-angle blunt cone model. Heat flux measurement was carried out on cone model at different angles of attack with angle of rotation ϕ = 0° to 360° in steps of 45° with vacuum sputtered platinum thin film sensors. The measured experimental value of heat transfer data at stagnation point was compared with theoretical value estimated Fay and Riddell correlation. As angle of rotation was increased from ϕ = 0° to ϕ = 180°, the shock wave became closer to model surface due to high density ratio across the shock wave and consequently heat transfer rate became higher.

使用11.37°顶角钝锥模型，在国防研究与局实验室的高超声速冲击隧道中以7.25的高超声速马赫数进行了实验。 使用真空溅射铂薄膜传感器，在锥角模型上以45°的旋转角ϕ = 0°至360°，以不同的迎角对热通量进行测量。将停滞点处传热数据的测量实验值与理论值估计的Fay和Riddell相关性进行了比较。随着旋转角度从ϕ  = 0°增大到ϕ  = 180°，由于在冲击波上的高密度比，冲击波变得更接近模型表面，因此传热率变得更高。