Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft

某型电动飞机大迎角失速/尾旋特性及试飞研究

¹ Liaoning Genral Aviation Acadeing, Shengyang Aerospace University, Shenyang 110136, China
² College of Aerospace Engineering, Nanjing University of Aeronations and Astronautics, Nanjing 210016, China

Received: 14 October 2020

Abstract

When the aircraft is flying at high angle of attack, the local separation of the air flow on the surface of the aircraft, the linear change of aerodynamic force is destroyed, and the maneuverability and stability are reduced to varying degrees, resulting in the aircraft stalling or entering the spin. The stall characteristics and spin characteristics directly affect the safety of the aircraft. In order to analyze the stall and spin characteristics, a full-scale 6-DOF nonlinear high angle of attack dynamic model is established for a two-seater electric high aspect ratio aircraft based on the wind tunnel test data. The stall characteristics of an electric aircraft at high angle of attack are obtained by numerical simulation and analysis. According to the stall characteristics of simulation calculation, flight test is carried out to verify the reliability of numerical simulation, which provides reference for the later analysis of stall/spin test of large aspect ratio series electric aircraft at nonlinear high angle of attack.

摘要

飞机在大迎角飞行时，其表面气流发生严重分离，气动力的线性变化遭到破坏，操纵性和稳定性出现不同程度下降，导致飞机失速或进入尾旋，失速特性与尾旋特性直接影响飞机的安全性。为了分析失速/尾旋特性，以某型大展弦比双座电动飞机为例，在风洞试验数据基础上建立了全量六自由度非线性大迎角动力学模型，经过数值仿真计算和分析，获取了某型电动飞机在大迎角下的失速/尾旋特性，根据仿真计算的失速/尾旋特性现象，进行飞行试验，验证了数值仿真的可靠性，为以后分析大展弦比系列电动飞机非线性大迎角下的失速/尾旋特性及试验研究提供参考。