DERIVATIVES OF A 60 ° DE15!A-WINGMODEL AS AFFECTED BY CHANGES IN VERTICAL POSITION OF THE WING AND IN RATIO OF FUSELAGE DIAMETER TO WIJ!JGSPAN

An investigation was made in the Lsngley stability tunnel to deter-mine the effects on the steady-state yawing derivatives of the vertical position of the wing for a 60 ° delta-wing model having ratios of fuselage. di-eter to wing span of 0.lJ?3,0.J-65,and 0.246. The test Mach number was 0.13 and the Reynolds nuniberwas 1.65 x 106. The results of the investigation indicated that for angles of attack below the stall the* steady-state darping in yaw decreased (the values of the yawing-moment coefficient due to yawing becsme less negative) when the wing was raised from a low to a middle or high position on each of the three fuselage sizes investigated. With the vertical tail on or off, the steady-state dsmping in yaw increased with an increase in fuselage size. The results of calculations of the oscillatory daqping in yaw for the model with the large fuselage indicated that the effects of’wing position would be oppo-site to those determined under steady-state conditions. For angles of attack below the stall, raising the wing produced a positive increment in the rolling moment due to yating, and fuselage size had little effect on this parameter