FLIGHT MEASUREMENTS WITH THE DOUGLAS D-558-E (BUAERO NO. 37974) RESEARCH AIRPLANE MEASUREMENTS OF THE DISTRIBUTION OF THE AERODYNAMIC LOAD AMONG THE WING, FUSELAGE, AND HORIZONTAL TAIL AT MACH NUMBERS UP TO 0.87

摘要

Flight measurements of the aerodynamic wing and tail loads have been made on the Douglas D-558-II airplane from which the distribution of the aerodynamic load among the wing, fuselage, and horizontal tail has been determined at Mach numbers up to 0.87.nThese measurements indicate that, for normal-force coefficients less than 0.7, the distribution of air load among the airplane com¬ponents does not change appreciably with Mach number at Mach numbers up to 0.87.nThe measurements also indicate that, for all flight configurations, the increase in airplane normal-force coefficient above the angle of attack at which the wing reaches its maximum normal-force coefficient is due principally to the contribution of the fuselage to the airplane normal-force coefficient.