Rapid evaluation method for aerodynamic characteristics of distributed electric propulsion aircraft concept scheme
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摘要:
分布式电推进（DEP）飞机充分利用气动/推进耦合效应提高飞机的气动效率，但动力数量增加导致螺旋桨滑流与翼面流场干扰强烈，气动分析和设计的复杂度及计算成本上升。为提高DEP飞机早期设计阶段气动设计效率，降低研制成本，采用线性无黏的涡格法-激励盘理论(VLM-ADT)、涡格法-非定常涡格法(VLM-UVLM)及加入黏性修正的VLM(Modified-VLM)提出气动特性快速评估方法。对单机翼、单螺旋桨/机翼耦合、X-57机翼(巡航、高升力状态)及分布式螺旋桨/机翼耦合构型的气动特性进行快速评估。与基于雷诺平均Navier-Stokes（RANS）方程求解器的结果对比，单机翼和单螺旋桨/机翼升力系数和阻力系数一致性良好，误差最大不超过8.2%；俯仰力矩系数在同一数量级。X-57机翼和分布式螺旋桨/机翼的升力系数与RANS方程结果吻合度较高，误差最大不超过10%。考虑黏性修正的VLM所计算的X-57机翼和分布式螺旋桨/机翼的总阻力系数与RANS方程结果趋势一致。分布式螺旋桨滑流增加机翼的动压，使机翼局部有效迎角发生改变，改变了机翼当地升阻特性。所提方法为分布式螺旋桨飞机在早期设计阶段气动特性快速评估和气动布局方案快速选型提供了一种兼顾计算精度和效率的有效方法。
Abstract:Distributed electric propulsion (DEP) aircraft makes full use of the aerodynamic/propulsion coupling effect to improve the aerodynamic efficiency of the aircraft, but the increase in the amount of power leads to strong interference between the propeller slipstream and the wing surface flow field, the complexity of aerodynamic analysis and design, and the rising costs of calculations. To improve the efficiency of aerodynamic design in the early design stage of DEP aircraft and reduce the development cost, a rapid evalution method of aerodynamic characteristics is proposed based on linear non-viscous vortex lattice method and actuator disk theory (VLM-ADT), VLM-unsteady VLM (VLM-UVLM) and Modified-VLM with viscosity correction. The aerodynamic characteristics of single wing, single propeller/wing coupling, X-57 wing (cruising, high lift state), and distributed propeller/wing coupling configuration were quickly evaluated. Compared with the Reyonlds-averaged Navier-Stokes (RANS) results, the lift coefficient and drag coefficient of single wing and single propeller/wing are in good agreement, and the maximum error does not exceed 8.2%; the pitch moment coefficient is in the same order of magnitude. The lift coefficients of the X-57 wing and the distributed propeller/wing are in good agreement with the RANS results, and the maximum error does not exceed 10%. The total drag coefficient of the X-57 wing and the distributed propeller/wing calculated by the VLM considering the viscosity correction is consistent with the trend of the RANS results. The distributed propeller slipstream increases the dynamic pressure of the wing, changes the local effective angle of attack of the wing, and changes the local lift-drag characteristics of the wing. Proposed method provides an effective method for the rapid evaluation of aerodynamic characteristics and rapid selection of aerodynamic layout schemes for distributed propeller aircraft in the early design stage.
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图 8 三种情况下的压力系数云图和流线图
Figure 8. Pressure coefficient nephogram and streamline of three kinds of circumstances
图 10 X-57高升力机翼升阻系数-迎角曲线
Figure 10. X-57 high-lift wing wing lift-drag coefficient-α curve
图 11 X-57分布式螺旋桨/高升力机翼升阻系数-迎角曲线
Figure 11. X-57 distributed propeller-high-lift wing lift-drag coefficient-α curves
图 12 有无动力状态X-57机翼表面压力系数对比
Figure 12. Comparison of X-57 wing surface pressure coefficient with and without power
图 13 有/无分布式动力X-57机翼展向升力系数分布
Figure 13. Spanwise lift coefficient of X-57 distribution with/without distributed power
图 14 X-57高升力机翼展向升力系数分布
Figure 14. X-57 high-lift wing spanwise lift coefficient distribution
表 1 计算构型1的几何参数
Table 1. Geometric parameters of calculated configuration 1
构型形成 参考弦
长/m翼展/m 机翼面
积/m2展弦比 螺旋
桨数目螺旋桨
直径/m单机翼 0.714 1 3.048 2.176 7 4.3 0 0 机翼/单螺
旋桨0.714 1 3.048 2.176 7 4.3 1 0.576 
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表 2 计算构型2的几何参数
Table 2. Geometric parameters of calculated configuration 2
构型
形成参考弦
长/m翼展/m 机翼面
积/m2展弦比 螺旋
桨数目螺旋桨
直径/mX-57
机翼0.65 9.627 6.193 9 15 0 0 X-57机
翼/分布
式螺旋桨0.65 9.627 6.193 9 15 12 0.576
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