Theoretical investigation of the effects of configuration changes on the center-of-pressure shift of a body-wing-tail combination due to angle of attack and mach number at transonic speeds

J. Richard Spahr
naca-tn-3966
May 1957


A theoretical investigation was made to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and in Mach number. This airframe was an unbanked canard missile configuration having low-aspect-ratio coplanar wing and tail surfaces of triangular plan form. Each of the following geometric parameters, which define the relative size, plan form, and position on the body of the wing and tail surfaces, was varied while the remaining parameters were held constant: (1) ratio of wing semispan to tail semispan, (2) ratio of body radius to wing semispan, (3) ratio of tail length to body length, (4) wing aspect ratio, (5) tail aspect ratio, (6) wing taper ratio, (7) tail taper ratio, (8) wing sweep, (9) tail sweep, (10) ratio of tail height (vertical distance of tail above body axis) to body radius, and (11) tail roll angle. An angle-of-attack range of 0 to 10 degrees and a Mach number range of 0.6 to 2.0 were covered in the investigation, and the theoretical method described and verified by experiment in NACA Rep. 1307 was used as a basis for the calculations.

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