WDPSS缩比模型的低速风洞测力试验

Force-Measuring Experiment for the Scale Model of WDPSS in Low-Speed Wind Tunnel

以满足风洞测力实验时所要求的缩比模型的姿态范围为出发点,进行低速风洞大攻角绳牵引并联支撑系统(WDPSS)的机构设计,得到构型WDPSS-8.研究WDPSS-8的缩比模型姿态控制技术和作用在缩比模型上的气动载荷的解算原理.在实现缩比模型的姿态控制和测力系统的基础上,对WDPSS-8进行开口式低速回流风洞吹风试验,得到一组升力系数、阻力系数及升阻比随攻角的变化曲线.虽然没有标模的试验数据对比,但所得的曲线是符合一般飞行器的空气动力特性的.

With the aim to satisfy the range of the attitude of the scale model required in the wind tunnel tests, a mechanism configuration of wire-driven parallel suspension systems （WDPSS） with large attack angle in low-speed wind tunnels,WDPSS-8, is given; and the attitude control technology of the scale model and the calculation principle about the aerodynamic force and torque exerted on the scale model is investigated; based on the attitude control experiment of the scale model and the implementation of the force-measuring system, a group of wind tunnel tests are done for the scale model of WDPPS-8 in an open return circuit low-speed wind tunnel and the experimental curves about lift coefficient versus angle of pitch, drag coefficient versus angle of pitch and lift/drag ratio versus angle of pitch are obtained. Though there is no data about the standard model as a criterion, the curves are suitable for expressing the aerodynamic characteristics of aircrafts.