Summary of Results Obtained by Transonic-Bump Method on Effects of Plan Form and Thickness on Lift and Drag Characteristics of Wings at Transonic Speeds

This paper presents a summszy of the ness on the lift and drag characteristics effects of plan form and thickof wings at transonic speeds.The data considered in this summary were obtain= during a transo~c reseerch progrsm conducted in the Lsngley high-speed ~-,by 10-foot tunnel by the transonic-bump method in the Mach number range from 0.6 to 1.15.The Reynolds numbers of the tests were generally less then 1 X 106.The results indicated that, for subsonic Mach numbers below the force break, theoretical lift-curve-slope calculations were in fair agreement with the experimental results, whereas in the supersonic range the theoretical values were considerably higher than the experimental values.Increasing w the thicl.messratiocaused rather lsrge losses of lift in the trsmsonic speed range and increasing the sweep angle decreased these losses.Decreasing the thickness ratio and increasing the sweep singleincreased .-thedrag-rise Mach number and reduced the pressure &sg.The sonic pressure drag vsried lineezly with the 5/3 power of the thichess ratio in accordance with the two-dimensional transonic similarity rule.The effect of sweep angle on the maximum pressure drag could also be estimated with good accuracy.In general, the drag due to lift was increaaed by decreaaes in thickness ratio, increases in sweep angle, and decreases in aspect ratio.