论文部分内容阅读
碟型飞行器采用了新颖的翼身融合气动布局。与常规飞行器相比,这种外形通过机身和机翼完全融合消除了机身阻力,且具有结构简单、容载大等许多优点,但由于其展弦比小而导致诱导阻力较大。本文通过风洞吹风试验,找到一种后掠鱼鳍形的翼尖小翼装置能很好地减小其诱导阻力。对模型安装翼尖小翼后,风洞测量其最大升阻比在 30 m/s 风速下提高了 75%,在50 m/s 风速下可达到 15。为进一步考察安装翼尖装置后的飞行器低速气动性能,对其进行了模型试飞研究。试飞验证了风洞吹风结果,不仅提高了载重量而且使横侧飞行稳定性增强。
Disc aircraft using a novel wing integration aerodynamic layout. Compared with the conventional aircraft, this shape completely eliminates fuselage resistance by fuselage and wing, and has many advantages such as simple structure and large capacity. However, due to its small aspect ratio, the induced resistance is larger. In this paper, wind-tunnel blowing test to find a fin-finned wingtip wing device can be very good to reduce the induced resistance. After the wingtip was installed on the model, the maximum lift-drag measured by the wind tunnel was 75% higher than at 30 m / s and 15 at 50 m / s. In order to further investigate the low-speed aerodynamic performance of aircraft after the installation of wingtips, a model test study was carried out. Flight test results verified wind tunnel results, not only to increase the load but also to enhance the stability of the lateral flight.