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为了研究等离子体环量控制对翼型的影响特性,采用基于唯象学的等离子体气动激励数学模型和二维雷诺平均N-S方程,选取NCCR 1510-7067N环量控制翼型,数值模拟后缘半径对升力和效费比的影响规律,并进行优化。设计最佳后缘半径模型进行低速风洞实验,获得迎角-4°~12°,速度6,10,15m/s下的压力分布和升力特性。研究表明:后缘半径过大或过小都不利于Coanda效应的产生,确定最佳后缘半径与弦长的比值为0.048,效费比97.69。低雷诺数下,随着迎角的增加,出现了层流长泡分离和短泡分离,等离子体射流不仅改善了尾部流场,还通过环量增加抑制层流分离,提高了升力。
In order to study the effect of plasma ring volume control on the airfoil, the aerodynamic excitation mathematical model based on phenomenology and the two-dimensional Reynolds averaged Navier-Stokes equations were used to select the NCCR 1510-7067N annular control airfoil and the numerical simulation trailing edge radius On the lift and cost-effectiveness of the law, and optimize. The optimum trailing edge radius model was designed for low-speed wind tunnel experiments to obtain the pressure distribution and lift characteristics under the attack angle of -4 ° ~ 12 ° and the speed of 6,10,15 m / s. The results show that the radius of the trailing edge is too large or too small, which is detrimental to the Coanda effect. The ratio of the optimal trailing edge radius to the chord length is 0.048, and the effective cost ratio is 97.69. Under the low Reynolds number, with the increase of the angle of attack, laminar long bubble separation and short bubble separation appear. The plasma jet not only improves the tail flow field, but also suppresses laminar flow separation and increases the lift by increasing the loop volume.