摘要: Models of two versions of the North American B-70 airplane were tested at Mach numbers of 2.5 and 3.0 at a Reynolds number of 5.0 million and at a Mach number of 3.5 at a Reynolds number of 4.5 million. Lift, drag, static-stabilit... 展开 Models of two versions of the North American B-70 airplane were tested at Mach numbers of 2.5 and 3.0 at a Reynolds number of 5.0 million and at a Mach number of 3.5 at a Reynolds number of 4.5 million. Lift, drag, static-stability, and control characteristics were determined for both complete models, for various components, and for various component modifications. Flow visualization studies were made with both natural and fixed boundary-layer transition. The data for the best configuration tested were extrapolated to give an all-turbulent lift-drag ratio for a Reynolds number of 110 million at a Mach number of 3.0. 收起