Force- and Pressure-Distribution Measurements on Eight Fuselages

The present report deals with force- and pressure-distribution measurements on a number of fuselage forms of varying slenderness ratio, varying rearward position of maximum thickness, and varying nose ratio. The effect of these parameters on the force and moment coefficients was determined. The linearity of the difference between the theoretical and experimental fuselage moments with the friction lift made it possible to indicate a neutral point and its travel with the different parameters. The pressure-distribution measurements yielded absolute values for the increase of velocity. A comparison with the theory indicated good agreement at small angles of attack, but considerable differences at greater angles of attack, where potential flow could no longer be assumed.