LONGITUDINAL AEXOD-YNAMI C CHARACTERISTICS To LARGE ANGLES CFMTACKOFA CRUCIFORMMISSIIJZ

uNgN;;:;-a;,Y& By autho~ti and drag characte&tics of a missile c configuration having a body of fineness ratio 9.33 and a cruciform tri-angular wing and tail of aspect ratio 4 were measured at a Mach number of 1.99 and a Reynolds number of 6.0 million, bas & on the body length. The tests were performed through an angle-of-attack range of-5O to 28' to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components. (body, King, and tail). Theoretical lift and moment characteristic.8 of the configuration and its components were calculated by the use of existing theoretical methods which.have been modified for application to high angles of attack, and these characteristics are com-pared tith experiment. The lift and drag characteristic8 of all combinations of the body, wing, and tail were independent of roll angle throughout the angle-of-attack range. The pftching-moment chara&eristics of the body-wing and body-wing-tail combinationa, however, were-%nfluenced significantly by the roll angle at large angles of attack (greater than loo). A roll from O " (one pair of wing panels horizontal) to 45 ' caueed a forward ehift ti the center of pressure which was of the same magnitude for both of these combinations, indicatingthatthLs shift originated frombody-wing inter-ference effecta. A favorable lift-interference effect (Wft of the combination greater than the sum of the l%fts of the coqonents) and a rearward shift in the center of pressure from a position corresponding to that for the compo-nents occurred at small angles of attack when the body was combined with. either the expoeed wing or tail surfaces. These lift and center-of-preseure interference effects were gradually reduced to zero as the angle of attack was increased to large values. ference, which influenced pr