一种跨声速风洞透气壁模型的数值模拟研究

宽体客机巡航状态、阻力发散马赫数状态以及俯冲状态的绕流均属于跨声速流动,风洞试验过程中由于试验段壁板的存在,模型与洞壁均可能产生较强的激波,并诱发复杂的相互干扰,进而呈现出强烈的非线性耦合现象。针对宽体客机标模在 FL灢26 风洞中试验的洞壁干扰情况,提出一种基于透气壁模型的数值模拟方法;基于该方法研究 0.8≤Ma ≤0.92 范围内的模型洞壁干扰耦合效应。结果表明:与基于壁压信息法的数值模拟方法相比,采用透气壁模型方法不需要测试数据,能够较好地模拟孔壁流动对宽体客机升力系数曲线的影响,同时也给阻力带来较大的修正量。

Numerical investigation on a porous wall model for the transonic wall interference

Flows past a wide-body aircraft operated at cruise, drag divergence and dive Mach numbers are transonic flows. When the aircraft model is tested in a transonic wind tunnel, strong shock wave may be induced due to the tunnel wall, which will incur the complex wall interference as a strong nonlinear coupling phenomenon. In order to investigate the wall interference to the standard model of a wide-body aircraft mounted in the FL-26 wind tunnel, a numerical simulation method based on a porous wall model was developed, and employed to research the interaction between the wall and the model at Mach numbers ranging from 0.8 to 0.92. Compared with the wall pressure information method, results obtained with the porous wall model indicate that the effect of the porous wall on the curve of lift coefficient can be captured better without measured data, but larger effect on the drag coefficient is produced.