Experiments were conducted on a micro air vehicle (MAV) model in a low speed wind tunnel to study the actual lift and drag experienced by the model under propeller inducedudflow by separating out the thrust force generated by the propeller by decoupling the motor-propeller from the model and mounting it on a second arrangement with minimaludflow interference. Tests were conducted on the model at actual flight conditions - at a freestream velocity of 9 m/s (Re = 135000 based on root chord) with the propellerudrunning at speeds ranging from 8000 to 10000 rpm. The lift and drag coefficients obtained from the model with decoupled motor-propeller arrangement are compared toudthose obtained from the model with attached motor-propeller for the same test conditions and justification is made in favor of the former method. Effects of propeller induced flow with respect to an increase in propeller rpm on the lift and drag characteristics of the model were also studied. Higher CL at higher angle of attack and increased CD were observed for the model under propeller induced flow. With an increase in propeller rpm, the effects seen in CL and CD are increased further.
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机译：在低速风洞中的微型飞行器（MAV）模型上进行了实验，通过分离螺旋桨产生的推力并通过分离电动螺旋桨来研究螺旋桨引起的 udflow下该模型所经历的实际升力和阻力从模型中将其安装在第二个装置上，以最小的溢流干扰。在实际飞行条件下以9 m / s的自由流速度（基于根弦，Re = 135000）对螺旋桨进行测试，螺旋桨以8000到10000 rpm的速度运转。在相同的测试条件下，将从具有解耦的电动机-螺旋桨布置的模型中获得的升力和阻力系数与从具有附加的电动机-螺旋桨的模型中获得的升阻系数进行比较，并证明采用前一种方法是合理的。还研究了螺旋桨诱导流量相对于螺旋桨转速的增加对模型的升力和阻力特性的影响。在螺旋桨诱导流下，模型在较高的攻角下具有较高的CL值，而CD则有所增加。随着螺旋桨转速的增加，在CL和CD上看到的效果进一步增加。
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