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针对带舵旋成体外形,来流马赫数为2.0,迎角为0°,10°和20°,喷口位于×字舵中间,首先开展了喷主流干扰流场的数值模拟与风洞实验校验,得到相符的喷口附近子午线压力分布,验证了数值模拟方法的可行性;然后根据数值模拟得到的喷主流干扰流场结构和流动参数分布,分析了喷主流干扰流场结构随迎角的变化特点;最后从喷口附近旋成体和尾舵表面压力分布的变化分析了喷主流干扰对气动力/力矩放大因子的影响.研究结果表明:随迎角增大,喷流前激波向喷口靠近,分离区减小,喷主流压比增大,喷流穿透高度增大;气动力/力矩放大因子均大于1.0,随迎角增大,放大因子减小.喷口位于×字舵中间时,喷主流干扰对喷流直接力有增益作用;×字舵的存在减弱了喷流的包裹作用,对流场起到了有利干扰.
For the body with rudder body, the Mach number is 2.0 and the angle of attack is 0 °, 10 ° and 20 °. The spout is located in the middle of the word rudder. First, the numerical simulation and wind tunnel experiment , The meridian pressure distribution near the nozzle is obtained and the feasibility of the numerical simulation method is verified. Based on the numerical simulation of the structure and flow parameter distribution of the main flow field, the structure of the main flow disturbance angle with the attack angle is analyzed Finally, the influence of the main jet interference on the aerodynamic / moment amplification factor was analyzed from the changes of the pressure distribution on the surface of the rotating body and the rudder surface near the discharge port.The results show that with the increasing angle of attack, the pre-jet shock wave approaches the orifice and separates Area decreases, the main pressure ratio increases, the jet penetration height increases; aerodynamic / torque amplification factor is greater than 1.0, with the angle of attack increases, the enlargement factor decreases.The nozzle is located in the middle of the word rudder, spray the mainstream The interference has a gain effect on the direct jet force; the existence of the x-helix weakens the jet’s package effect, which has a favorable interference to the flow field.