The aerodynamic forces and pressure distribution of a revolving pigeon wing.
The aerodynamic forces and pressure distribution of a revolving pigeon wing.
复制标题
DOI：
10.1007/s00348-008-0596-z
复制
发表时间：
2009-05
影响因子：
2.4
通讯作者：
Usherwood, James R.
中科院分区：
文献类型：
--
作者：
Usherwood, James R.
利用螺旋桨装置测量了旋转干鸽翼和平卡复制品的气动力，有效地模拟了机翼连续下冲程。采用了两种方法：一种是通过力板直接测量反作用力和扭矩，另一种是通过差压传感器测量机翼上和机翼上的压力。翅膀在高达108,000的雷诺数下进行了测试，这是慢速飞行的鸽子的典型雷诺数，大大高于之前用于昆虫和蜂鸟翅膀和翅膀模型的类似测量。鸽子翅膀的升力系数达到了1.64，超过了平卡复制品的1.44。真实和模型机翼都获得了更高的最大升力系数，并且具有更高的几何迎角（43°），比在风洞中模拟翻译飞行的机翼测试所期望的更高。因此，一些可能类似于慢速飞行昆虫的高升力机制，可能适用于以大攻角扇动翅膀的鸟类。作用在旋转鸽子翅膀上的空气动力的净大小和方向可以从压差图中以中等程度的精度确定。随着迎角的增大，在33°~ 38°的迎角范围内，接近垂直力系数或升力系数最高的角度，压力信号的变异性突然增大；与风洞中机翼的测量结果相比，失速似乎是延迟的。
The aerodynamic forces acting on a revolving dried pigeon wing and a flat card replica were measured with a propeller rig, effectively simulating a wing in continual downstroke. Two methods were adopted: direct measurement of the reaction vertical force and torque via a forceplate, and a map of the pressures along and across the wing measured with differential pressure sensors. Wings were tested at Reynolds numbers up to 108,000, typical for slow-flying pigeons, and considerably above previous similar measurements applied to insect and hummingbird wing and wing models. The pigeon wing out-performed the flat card replica, reaching lift coefficients of 1.64 compared with 1.44. Both real and model wings achieved much higher maximum lift coefficients, and at much higher geometric angles of attack (43°), than would be expected from wings tested in a windtunnel simulating translating flight. It therefore appears that some high-lift mechanisms, possibly analogous to those of slow-flying insects, may be available for birds flapping with wings at high angles of attack. The net magnitude and orientation of aerodynamic forces acting on a revolving pigeon wing can be determined from the differential pressure maps with a moderate degree of precision. With increasing angle of attack, variability in the pressure signals suddenly increases at an angle of attack between 33° and 38°, close to the angle of highest vertical force coefficient or lift coefficient; stall appears to be delayed compared with measurements from wings in windtunnels.
登录
查看更多内容
影响因子：
2.8
作者：
Hedrick, T. L.;Daniel, T. L.
通讯作者：
Daniel, T. L.
DOI：
10.1098/rstb.1984.0049
发表时间：
1984-01-01
影响因子：
6.3
作者：
ELLINGTON, CP
通讯作者：
ELLINGTON, CP
影响因子：
2.8
作者：
Usherwood, JR;Hedrick, TL;Biewener, AA
通讯作者：
Biewener, AA
影响因子：
2.8
作者：
Dickson, WB;Dickinson, MH
通讯作者：
Dickinson, MH
影响因子：
2.8
作者：
Berg, Angela M.;Biewener, Andrew A.
通讯作者：
Biewener, Andrew A.