| 摘要 |
An angle of attack indicator for use as a cockpit instrument including movable elements which respond to the differences in pressure at various points on the leading edge of the aircraft wing. The operation of the indicator is based on the principles that (1) as the angle of attack of the wing is increased, the point of maximum pressure on the wing moves down around the leading edge thereof, and (2) in the region of the point of maximum pressure, the pressure decreases as one moves away from the point of maximum pressure.
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