The jet control effectiveness of a 5 deg semi-angle cone has been tested at hypersonic speeds. The study has beencarried out in the Cranfield hypersonic gun tunnel facility at a Mach number of 8.2, and a Reynolds number based onbase diameter of 3.788 x 10(5). Under those conditions, the initial boundary layer in the absence of the jet was laminar.The jet was injected normal to the cone surface at sonic speed. Both sharp and blunted cones were used. TheJet/flowfield interaction, including boundary-layer separation and its influence upon aerodynamic coefficients wasdetermined. Pressure and force measurements were made in the incidence range of -15 deg to 15 deg. The forces weremeasured with a 3-component balance equipped with semi-conductor strain gauges. The flow structure was studiedusing high speed schlieren photography. Jet penetration distances have been compared with theoretical estimates.
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机译：5度半角锥的射流控制效果已在高超声速下进行了测试。该研究是在克兰菲尔德高超音速炮管设施中进行的，其马赫数为8.2，雷诺数基于基径为3.788 x 10（5）。在这些条件下，没有射流的初始边界层是层流的。以声速垂直于锥面注入射流。尖锥和钝锥都使用。确定了Jet /流场相互作用，包括边界层分离及其对空气动力学系数的影响。在-15度到15度的入射范围内进行压力和力的测量。用装有半导体应变仪的三分量天平测量力。使用高速schlieren摄影研究了流动结构。射流穿透距离已与理论估计值进行了比较。
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