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以高空长航时(HALE)太阳能无人机(UAVs)研究为背景,采用基于混合网格技术及k-kL-ω转捩模型求解雷诺平均Navier-Stokes(RANS)方程的多重参考系(MRF)方法,对3种螺旋桨-机翼构型的低雷诺数气动特性进行了高精度准定常数值模拟,在等拉力前提条件下,通过对比机翼气动力系数及表面流场结构特征分析了分布式螺旋桨(DEP)滑流对FX63-137机翼的气动影响。研究表明:螺旋桨滑流影响使得桨后总压及流速显著增大,这是机翼升力增大的主要原因,但同时机翼阻力特性急剧恶化,升阻比反而降低;螺旋桨滑流向机翼边界层内注入丰富湍动能从而抑制流动分离,扩大机翼表面湍流范围及附着流动区域;分布式螺旋桨滑流与低雷诺数机翼表面复杂流动相互作用显著,主要表现为滑流区域边界展向涡结构的产生。
Based on the study of HALE solar unmanned aerial vehicles (UAVs), a multiple reference frame (MRF) based on hybrid grid technique and k-kL-ω transition model for solving the Reynolds-average Navier-Stokes (RANS) ) Method, the low-Reynolds number aerodynamic characteristics of three kinds of propeller-wing configurations are simulated with high-precision quasi-constant constants. Under equal tension preconditions, the distribution of the aerodynamic coefficients and the structural characteristics of the surface flow field is analyzed Aerodynamic effects of propeller (DEP) slipstream on wing of FX63-137. The results show that propeller slippery flow makes the total pressure and flow velocity significantly increase, which is the main reason for the increase of wing lift, but at the same time, the resistance characteristics of the wing deteriorate sharply, while the lift-drag ratio decreases. On the other hand, The rich turbulent kinetic energy was injected into the layer to suppress the flow separation and enlarge the turbulence area and the attached flow area on the wing surface. The interaction between distributed propeller slipstream and complex Reynolds number wing surface was significant, Structure generation.