Abstract
The propeller slipstream effect is one of the powerful means to improve the STOL characteristics of a propeller airplane, in the same way as the high lift device that is flap or boundary layer control, etc. and therefore we have several airplane which utilize its effect (Breguet-941, PX-S). For the Tilt Wing VTOL (XC-142, CL-84), in which the propeller slipstream effect is utilized, the STOL characteristics is important in its operation. In general, the propeller slipstream effect can not be avoided in a low speed flight of the propeller airplane. This wind tunnel tests have been carried out for the purpose to investigate the various effects that the propeller slipstream influences on the airplane characteristics and the aerodynamic difficulties that we encounter in its practical applications, using a deflected slipstream airplane. It has been suggested by the wind tunnel test results that the airplane which utilize the propeller slipstrem, may have the following peculiar properties. (1) the longitudinal static instability (2) the directional static instability and the nonlinear yawing moment (3) the discontinuity of the rolling moment (4) the deterioration of the dihedral effect (5) the deficiency of the control power when one engine loses power (6) the nonlinearity of the control effectiveness
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