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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1983, Vol. 4 ›› Issue (1): 16-21.

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EQUIVALENT ANGLE OF ATTACK FOR THE LIFTING PLANE WITH LINEAR CAMBER-TWIST AT LOW SPEEDS

Xu Daming   

  1. Harbin Aerodynamic Institute
  • Received:1982-09-08 Revised:1900-01-01 Online:1983-03-25 Published:1983-03-25

Abstract: A law for 3-dimensional wing is provided on the basis of a matrix method.Formula(1)is its basic equation,and the definition of the equivalent angle of attack αv is given by formula(7).[A]denotes the vortex introduced matrix and [AT]——the reverse-flow introduced matrix.The equivalent angle ofattack for the whole wing with linear camber-twist can be given by equations(23),(24),(25),(26),where X0,Z0 are coordinates of the aerodynamic center in reverse flow.The above conclusion is capable of substitution for the two-dimensional Pistolesi theorem.