Flight investigation of the effect of tail configuration on stall, spin, and recovery characteristics of a low-wing general aviation research airplane
Flight investigation of the effect of tail configuration on stall, spin, and recovery characteristics of a low-wing general aviation research airplane
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尾部布局对低翼通用航空研究飞机失速、自旋和恢复特性影响的飞行研究
DOI：
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发表时间：
1987
期刊：
影响因子：
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通讯作者：
S. Sliwa
中科院分区：
文献类型：
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作者：
H. P. Stough;J. M. Patton;S. Sliwa
进行了飞行测试，以调查低翼，单引擎，轻型飞机具有四个可互换尾巴配置的摊位，自旋和恢复特性。评估了四个尾构型的质量分布，重心位置和控制输入的影响。飞机倾向于在摊位上滚动。尾配置的变化产生的旋转范围从40度到60度的攻击角，转弯速率约为145至208度/秒。遇到了一些无法恢复的扁平旋转，这些旋转需要使用飞机旋转槽进行恢复。对于可回收的旋转，安匹吡金方向舵，然后是前轮，以副翼为中心，提供了最快的自旋恢复。中等自旋模式与自旋隧道模型测试预测的旋转模式非常吻合，但是，平面自旋的攻击角度低于模型测试所示的较低的旋转速率。
Flight tests were performed to investigate the stall, spin, and recovery characteristics of a low-wing, single-engine, light airplane with four interchangeable tail configurations. The four tail configurations were evaluated for effects of varying mass distribution, center-of-gravity position, and control inputs. The airplane tended to roll-off at the stall. Variations in tail configuration produced spins ranging from 40 deg to 60 deg angle of attack and turn rates of about 145 to 208 deg/sec. Some unrecoverable flat spins were encountered which required use of the airplane spin chute for recovery. For recoverable spins, antispin rudder followed by forward wheel with ailerons centered provided the quickest spin recovery. The moderate spin modes agreed very well with those predicted from spin-tunnel model tests, however, the flat spin was at a lower angle of attack and a slower rotation rate than indicated by the model tests.