分布式电推进飞机概念方案气动特性快速评估方法  

Rapid evaluation method for aerodynamic characteristics of distributed electric propulsion aircraft concept scheme

作　　者：成志勇 杨佑绪 张兴翠 余灵富 叶博 CHENG Zhiyong;YANG Youxu;ZHANG Xingcui;YU Lingfu;YE Bo(School of Flight Vehicle Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《北京航空航天大学学报》2023年第11期3047-3058,共12页Journal of Beijing University of Aeronautics and Astronautics

基　　金：江西省“双千计划”人才项目(CK202006470);南昌航空大学研究生创新专项资金项目(YC2021-049)。

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。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.

关 键 词：分布式电推进 涡格法 非定常涡格法 激励盘理论 螺旋桨滑流 气动干扰 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]