NACA RESEARCH MEMORANDUM LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A MODEL AIRPLANE CONFIGURATION EQUIPPED WITH A SCALED X-1 AIRPLANE VING

NACA RM L511,10a NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS RESEARCH MEMORANDUM LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF AMODEL AIRPLANE CONFIGURATION EQUIPPEDWITH A SCALED X-1 AIRPLANE WING By James H. Parks SUMMARY Results are presented of an investigation at Mach numbers from 0.60 to 1.11 of a rocket-propelled model of an airplane configuration equipped with a scaled X-1 wing of 8-percent-thickness ratio. The data were obtained by analyzing the response of the model to abrupt horizontal-tail deflections. Some effects of adding the wing to the fuselage-tail configuration were determined. The analysis indicated nonlinearity of the lift-curve slope and static-stability characteristics.thirough the entire Mach number range, though the effects were more pronounced at subsonic speeds. Substantial losses in lifting ability were noted at transonic speeds. Buffeting was indicated at lift coefficients slightly below maximum up to Mach num-ber 0.80. Between Mach numbers of 0.80 and 0.91 severe buffeting occurred at lift coefficients well below the maximum. The configuration exhibited a high minimum drag which was reflected in a low maximum lift-drag ratio. Leading-edge suction is indicated at subsonic speed but gradually approaches zero as the Mach number is increased. Although the stability derivatives varied erratically with Mach number and lift coefficient, a high degree of static stability was exhibited through the entire Mach number range. The damping derivatives varied irregularly with Mach number and lift coefficient but the damping was effective even when the model oscillated through complete stalls. The all-movable tail is shown to be an effective device for changing lift, angle of attack, and pitching moment over the entire speed range and little change in control deflection would be necessary to maintain level-flight conditions from M = 0.90 to M = 1.10. INTRODUCTION The results of one phase of a general research program to determine by means of rocket-propelled vehicles in free flight the effects of various wings on the longitudinal stability, control, drag, and buffeting