Experimental Investigation of the Effects of Aerospike Geometry on Aerodynamic Drag and Heat Transfer Rates for a Blunt Body Configuration at Hypersonic Mach Numbers

S. Srinath, K. Reddy
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引用次数: 14

Abstract

The effects of aerospike geometry on the drag reduction and heat transfer rates for a large-angle blunt cone flying at hypersonic Mach numbers are investigated in a hypersonic shock tunnel. Two spike geometries are considered. The first is a plain spike with a conical tip and the second is a telescopic aerospike fitted with discs of decreasing diameter in the direction opposite to the flow direction. These aerospikes are fitted to a 120° apex-angle blunt cone and results are investigated at free stream Mach numbers of 5.75 and 7.9 for different angles of attack. The aerodynamic forces are measured using an accelerometer-based force balance system and the heat transfer rates are measured using platinum thin film sensors. It is found that the telescopic aerospike has better drag reduction performance at angles of attack beyond 2° while the performance of the plain aerospike is better for angles of attack closer to zero degrees.
高超声速马赫数下钝体构型气动阻力和换热率影响气动刺几何形状的实验研究
在高超声速激波隧道中,研究了气动刺几何形状对大角钝锥在高超声速马赫数下飞行的减阻和换热率的影响。考虑了两种尖峰几何形状。一种是带锥形尖头的普通尖头,另一种是与流动方向相反方向上装有直径递减圆盘的伸缩尖头。在不同攻角的自由流马赫数分别为5.75和7.9的情况下,研究了不同攻角下的气动尖刺安装在120°尖角钝锥上的结果。空气动力采用基于加速度计的力平衡系统测量,传热率采用铂薄膜传感器测量。研究发现,伸缩式气动杆在迎角大于2°时具有较好的减阻性能,而普通气动杆在迎角接近0°时具有较好的减阻性能。
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