THE INFLUENCE OF THE PROPELLER POSITION ON THE AERODYNAMICS OF A CHANNEL WING
THE INFLUENCE OF THE PROPELLER POSITION ON THE AERODYNAMICS OF A CHANNEL WING
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螺旋桨位置对通道翼空气动力学的影响
DOI：
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发表时间：
2013
期刊：
影响因子：
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通讯作者：
R. Radespiel
中科院分区：
文献类型：
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作者：
L. Müller;D. Kožulovi;M. Hepperle;R. Radespiel
本文研究了关于空气动力学对设计参数的敏感性的通用通道机翼配置。数值模拟包括通道深度的变化、螺旋桨的弦向位置以及简化机翼和致动器盘几何形状的间隙。机翼升阻比和螺旋桨效率的评估表明几何参数和空气动力学性能之间存在复杂的依赖性。显然，具有大嵌入深度和最小间隙尺寸的高度集成设计会对机翼产生最有利的影响，但对螺旋桨产生不利影响。由于推进系统总是受到这种装置的影响，因此相互影响不具有协同性。在评估考虑执行器盘上的推力损失的校正升阻比时，整体配置的品质因数仅受三个设计参数的影响很小。更具体地说，当瞄准高爬升角度时，较不紧密的耦合被认为是有利的。加上预期的屏蔽能力，起飞时的小噪音足迹可以通过空气动力学驱动的措施间接实现。术语 b、s 翼展、半展 c 弦长 cl、cd 局部升力、阻力系数 cμ 喷流动量系数 CT 飞机推力系数 d 螺旋桨叶尖与机翼表面之间的间隙 DP 螺旋桨直径 D、CD 阻力、飞机阻力系数 L、CL 升力、飞机升力系数 Ma 马赫数 n 螺旋桨轴转速 p、cp 静压、压力系数 PS、CP、s 螺旋桨轴功率、功率系数 q∞、ρ∞ 动压、密度(自由流) Re 雷诺数 Sref 参考飞机机翼面积 T, t/t 一台发动机的最大推力，相对局部推力 V 流速 W 飞机起飞重量 x, y, z 笛卡尔坐标 y 无量纲壁坐标 α 攻角 (AOA) αe 桨叶有效攻角 P, Pro 螺旋桨效率、推进效率 θ 爬升角 下标安装（推力）隔离(推力) j jet (喷嘴出口处)
The paper investigates a generic channel wing configuration regarding the aerodynamic sensitivities to design parameters. Numerical simulations include a variation of the channel depth, the chordwise position of the propeller and clearance for the simplified wing and actuator disk geometry. Evaluation of the lift-to-drag ratio of the wing and the propeller efficiency indicate complex dependencies between geometric parameters and aerodynamic performance. It is evident that a highly integrated design with large embedding depth and minimum gap size leads to most beneficial influences on the wing but an adverse effect on the propeller. As the propulsion system always suffers from this kind of installation, the mutual influence is not of synergistic nature. Evaluating a corrected lift-to-drag ratio which takes the thrust loss on the actuator disk into account, the figure of merit of the overall configuration is only little affected by the three design parameters. More specifically, a less close coupling is considered advantageous when aiming at high climb angles. Together with the expected shielding capabilities, a small noise footprint at take-off can be indirectly achieved through aerodynamically driven measures. Nomenclature b, s wing span, semispan c chord length cl, cd local lift, drag coefficients cμ jet momentum coefficient CT aircraft thrust coefficient d gap between propeller tip and wing surface DP propeller diameter D, CD drag, drag coefficient of aircraft L, CL lift, lift coefficient of aircraft Ma Mach number n propeller shaft speed p, cp static pressure, pressure coefficient PS, CP,s propeller shaft power, power coefficient q∞, ρ∞ dynamic pressure, density (free-stream) Re Reynolds number Sref wing area of reference aircraft T, t/tmax thrust of one engine, relative local thrust V flow velocity W aircraft take-off weight x, y, z Cartesian coordinates y dimensionless wall coordinate α angle of attack (AOA) αe effective angle of attack at blade element P, Pro propeller efficiency, propulsive efficiency θ climb angle Subscripts inst installed (thrust) isol isolated (thrust) j jet (at nozzle exit)