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采用风洞冷流试验方法研究了使用塞式喷管的运载器在4个典型飞行马赫数下外流对运载器流场和性能的影响。试验模型由截短的线性塞武喷管和升力体构成,利用纹影显示技术得到了塞式喷管流场结构并测量了不同试验工况下模型的轴向力和升力。结果表明:外流使塞式喷管喷流的膨胀程度变大,横向侧流强度增强;外流干扰下塞式喷管的推力损失包括过膨胀损失和横向侧流损失,试验喷管总推力损失在4.7%~9.6%之间,其中过膨胀损失在3%以内。
The cold flow test in wind tunnel was used to study the influence of outflow on the flow field and the performance of the carrier under the four typical flight Mach number. The experimental model consists of a truncated linear plug nozzle and a lifting body. The flow field structure of the plug nozzle is obtained by using the shadow display technology and the axial force and lift of the model under different test conditions are measured. The results show that the outflow causes the degree of expansion of the nozzle jet to be larger and the lateral side flow to increase. The thrust loss of the plug nozzle includes the over-expansion and lateral side-flow losses. The total thrust loss of the test nozzle is between 4.7% ~ 9.6%, of which over-swelling loss of less than 3%.