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Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
An N.A.C.A. 23012 rectangular wing with rounded tips was tested in combination with a fuselage of circular cross section at several angles of yaw in the N.A.C.A. 7- by 10-foot wind tunnel. The model was tested as a high-wing, a midwing, and a low-wing monoplane; for each wing location, tests were made with two amounts of dihedral and with partial-span split flaps. For each combination of wing and fuselage, tests were made with and without a fin. Sample charts of the coefficients of rolling moment, yawing moment, and lateral force are given for some of the combinations tested. THe rate of change in the coefficients with angle of yaw is given for stability calculation.
Presented are lift, drag, and pitching-moment data, neutral points, and the effects of power, flap deflection, and free elevator for the model at zero angle of yaw. The lateral-stability parameters and tests for a yaw range including rudder-free data are also presented.
A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established.