头部钝度和尾部形状对空射火箭气动特性的影响

摘要

To study the rule of different shape affecting the aerodynamic characteristics of air-launched rocket,the experiments in low-speed wind tunnel were carried out at the angle of incidence range of 0 - 80° and the speed of 17 m/s,25 m/s,35 m/s and 40 m/s.Forces and moments were measured through six-component balance.The result shows that vortex asymmetry appears under the conditions of zero side slip.Asymmetrical phenomenon leads to larger side force and yaw moment.In addition,variation of the pitching moment with angle of attack shows instability at some incidences.The longitudinal stability of the model with convergent-expanded afterbody is improved compared to cylindrical afterbody.The maximum side force of the blunt nose model with 6% bluntness is reduced at least by 50%,and the onset angle for vortex asymmetry is increased by 7°.The results offer some references for designing the cabin air-launched rocket.%为了研究空中发射运载火箭外形对气动特性的影响规律,通过低速风洞实验,利用六分量天平测量空射火箭模型在迎角0~80°,4个速度(17 m/s,25 m/s,35 m/s,40 m/s)下的气动力和气动力矩。结果表明：在零侧滑条件下,模型的背风区出现了非对称涡,产生较大的侧力和偏航力矩,俯仰力矩随迎角的变化存在不稳定区域；相比圆柱形尾部模型,收敛扩张形尾部提高了模型的纵向稳定性,6%头部钝度的圆头模型最大侧力减少至少50%,非对称涡的起始迎角提高了7°。研究结果可为内装式空射火箭的外形设计提供一定的参考。