摘要
3.2 失速特性失速特性试飞是在巡航（襟翼收上,起落架收上）、起飞（襟翼15°,起落架收上）和着陆（襟翼38°,起落架放下）三种构形下,后重心28％b<sub>A</sub>,飞机质量为21.4～19.7t范围内进行的。慢车直线飞行失速特性试验的发动机油门为17°,扭矩压力为1.9 MPa。带动力直线飞行和转弯飞行失速特性试验的发动机功率为1.6V<sub>s1</sub>平飞功率,即油门为30°,扭矩压力约为3.0MPa。失速特性试验的后重心改在28％b<sub>A</sub>,而不是在设计后重心33％b<sub>A</sub>。
The stall flight test for airworthiness certification of Y-7 aircraft is a danger item and this work was done completely according to CCAR25 first time in China by Chinese pilot arid engineers. In this paper, the test aircraft, the flight test method and procedure. the measurement technique as well as the data processing method are introduced briefly, Also, the stall speed and characteristics flight results of Y-7 aircraft in three configuration are detailed, All these results introduced in this paper may be very useful to aircraft designer, flight test researcher and air crew member.
出处
《飞行力学》
CSCD
北大核心
1993年第1期59-59,65,共2页
Flight Dynamics
