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给出了一种新型分布型人工转捩粗糙元设计技术,该技术解决了传统人工转捩方法在跨声速风洞试验中存在的效率低、可靠性和重复性差等问题。通过理论研究确定了该转捩技术的形式,包括粗糙元形状、高度和排列方式等技术参数以及针对不同模型的设计方案;同时对翼型模型(NACA0012)和全机模型(GBM-01或AGARD-B标模)在不同马赫数和迎角下分别进行了测压和测力风洞试验,借助升华法,对人工转捩技术的边界层转捩效果进行了验证研究。结果表明:在不同模型上使用不同的设计方案,该转捩技术可以得到可靠的固定转捩效果,并获得具有大气飞行中高雷诺数特点的气动力结果。
A new type of distributed artificial turret rough element design technique is presented. This technique solves the problems of low efficiency, poor reliability and poor reproducibility of the traditional artificial turret method in transonic wind tunnel tests. Through the theoretical study, the form of the transitional technique is determined, including the technical parameters of the roughness element shape, height and arrangement, and the design scheme for different models. Meanwhile, the airfoil model (NACA0012) and full-machine model (GBM-01 or AGARD B model) under different Mach number and angle of attack were carried out wind pressure test and wind tunnel test, with sublimation method, the artificial transfer 术 technology boundary layer transition effect was verified. The results show that, using different design schemes in different models, the transfer technology can obtain reliable fixed transfer results and obtain the aerodynamic results with high Reynolds number in the atmosphere.