WIND-TUNNEL/FLIGHT CORRELATION STUDY OF AERODYNAMIC CHARACTERISTICS OF A LARGE FLEXIBLE SUPER¬SONIC CRUISE AIRPLANE (XB-70-1). II - EXTRAPOLATION OF WIND-TUNNEL DATA TO FULL-SCALE CONDITIONS

摘要

This report contains the results of calculations necessary to extrapolate performance data on an XB-70-1 wind-tunnel model to full scale at Mach numbers from 0.76 to 2.53. The extrapolation was part of a joint program between the NASA Ames, Langley, and Dryden Flight Research Centers to evaluate present-day performance prediction techniques for large flexible supersonic airplanes similar to a supersonic transport. The extrapolation procedure included:interpolation of the wind-tunnel data at the specific conditions of the flight test points;determination of the drag increments to be applied to the wind-tunnel data, such as spillage drag, boundarylayer trip drag, and skin-friction increments;and estimates of the drag items not represented on the wind-tunnel model, such as bypass doors, roughness, protuberances, and leakage drag. In addition, estimates of the effects of flexibility of the airplane were determined.