Wind Tunnel Tests on a Low-Wing Monoplane With Propeller Running

Various tests have been conducted on airplane wind tunnel models with an operating propeller in an endeavor to furnish the industry data as an aid in design and performance predictions. At the GALCIT, these investigations have comprised the material set forth in references 1, 2 and 4. The tests conducted by the authors of this paper represent a continuation of the above-mentioned investigations. The purpose of the present tests was to determine l) the effect of power on static longitudinal stability (elevator free); 2)·the effect of power on hinge moments (at various tab angles); and 3) the effect of power on static directional stability with the model operating at high and low angle of attack.