考虑间隙内流的二元机翼跨声速气动力分析

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.

Transonic aerodynamic loads of airfoil considering internal flow of gaps

Based on the Navior-Stokes equation and Spalart-Allmaras turbulence model,the aerodynamic model of airfoil with internal flow in gaps is established to simulate the transonic flow field of ceramic tiles.The pressure and Mach number distributions of airfoil are obtained by numerical simulation using Fluent.The results are verified by comparing with the data from wind tunnel tests.The numerical results show that the internal flow exists when there are gaps connecting the high pressure zone after the shock and the low pressure zone before the shock.The internal flow in the gaps increases the local air speed gradient and pressure gradient around the airfoil near the shock.For the isolated area in the airfoil which simulates the tile,the aerodynamic loads from the internal flow of gaps are tend to "suck off" and "push" the isolated structure surrounded by the gaps.