【摘要】 为研究高速飞行器在高超声速来流条件下侧向喷流干扰效应,在CARDC-2m激波风洞上采用“先内流,后外流”的总体技术方案,完成了双锥模型在M6~M10,模拟高度20km~40km,有侧向喷流条件下的测压、测力试验研究,并采用高速流场显示方法进行了流场纹影照相。喷流模拟装置为路德维希管,冷喷流采用氮气,热喷流采用氢氧燃烧的高温气体,喷流有效时间不少于50ms。试验气流为激波风洞产生的高超声速氮气流,有效试验时间为4ms~20ms。试验研究获得了模型攻角在-10°~10°之间,不同的马赫数、高度和侧向喷流状态下的相关试验结果。本文给出了试验数据曲线和流场纹影照片,并对结果进行了初步分析和讨论。更多还原

【Abstract】 The paper presents the wind tunnel test study for side jet interaction effects in CARDC- 2m Shock Tunnel according to the test scheme of wind tunnel flow after jet flow. Jet flows, both cold and hot jet flows, are provided by a Ludwig tube. The cold jet gas is nitrogen pumped into the Ludwig tube at room temperature. For simulating hot jet flows, nitrogen is heated by hydrogen and orygen. The available time of jet flows is no less than 50ms. There are 4ms～20ms hypersonic nitrogen flow produced by the shock tunnel. The flow conditions are: Mach number: M=6～10,altitude: H=20km～40km.The test model is a dual-cone one and attack angle is -10°～10°. The test show the results of the aerodynamic forces and pressure measurements and schlieren photos under different side jet interaction conditions and different flow field conditions to meet the needs of the missile research.更多还原