战术导弹横向喷流数值模拟

为了研究喷流对导弹不同升力面的干扰影响,通过数值求解N-S方程来模拟超声速外流场中横向喷流的干扰流场,采用分块对接网格和"O"型网格技术,精确模拟喷口截面及弹翼形状,生成高质量的贴体计算网格.通过几种升力面和弹身组合的超声速横向喷流干扰流场的数值模拟,计算的马赫数为2和4.5,计算结果显示具有升力面的喷流干扰比光弹身的喷流干扰大.研究和分析了喷口附近流场的涡系结构和波系结构,并将导弹喷流干扰力放大因子及喷流引起的压心变化的计算结果与目前国外公布的试验值进行比较分析,二者显示了良好的一致性.

Numerical investigation of supersonic jet interactions for tactical bodies

In order to investigation of the jet interaction for finned bodies, the interact ion between a lateral jet and the supersonic external flow was investigated nume rically by solving the N-S equation. To model more exactly the nozzle geometry and resolve the complex flow associated with the lateral jet proble m,the multi-block point matched grid generation technique and "O" type grid t echnique were applied. The detailed numerical simulation for a variety of missil e geometries in the supersonic flow was performed. These include nonfinned axisym m etrical bodies and finned bodies with either strakes or aft-mounted tail fins. T he computations were performed at Mach numbers 2 and 4.5. The computational resu lts show significant interactions of the jet induced flowfield with the fin surf aces that produce additional effects compared with the body alone. The computati onal results were compared with the experimental results from a previously publi shed wind-tunnel study that consisted primarily of global force and moment meas u rements. The numerical calculations show good agreement with the experimental investigation at supersonic Mach numbers.