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基于Navior-Stokes(N-S)方程和Spalart-Allmaras湍流模型,建立了含间隙二元机翼的跨声速绕流场计算模型和间隙内流计算模型。通过FLUENT数值仿真,分析了二元机翼的激波压力分布和马赫数分布,并与风洞试验结果进行了对比验证。数值结果表明,连通波后高压区和波前低压区的间隙内流会提高机翼绕流场中激波前后的速度梯度和压力梯度。局部间隙内流会对机翼结构带来“向外吸”和“向前顶”的气动载荷作用。
Based on the Navior-Stokes (N-S) equation and the Spalart-Allmaras turbulence model, a transonic flow field calculation model and an interstitial flow model are established. By FLUENT numerical simulation, the shock pressure distribution and Mach number distribution of the binary wing are analyzed and compared with the wind tunnel test results. The numerical results show that the interflow gap between the high pressure area and the low pressure area increases the velocity gradient and the pressure gradient before and after the shock wave around the flow field. Local interstitial inflows can cause aerodynamic loads on the wing structure “outward suction ” and “forward ”.