wind-tunnel/flight correlation study of aerodynamic characteristics of a large flexible supersonic cruise airplane cxb-70-1). 1: wind-tunnel tests of a 0.03-scale model at mach numbers from 0.6 to 2.53

The longitudinal and lateral forces and moments for a 0.03 scale deformed rigid, static force model of the XB-70-1 airplane were determined. Control effectiveness was determined for the elevon in pitch and roll, for the canard, and for the rudders. Component effects of the canard, deflected with tips, variable position canopy, bypass doors, and bleed dump fairing were measured. The effects of small variations in inlet mass flow ratio and small amounts of asymmetric deflection of the wing tips were assessed.