Supersonic aerodynamic characteristics of a model of an air-to-ground missile

tv fo An investigation has been conducted to determine the aerodynamic characteristics of a model of an air-to-ground missile simulating both the boost-and glide-phase configurations.The results include the effects of fin size and sweep angle as well as the effects of the size and deflection of the control wings.The investigation was conducted" for model roll angles of 0° and 45° at Mach numbers of 1.60 and 2.00 at a Reynolds number of 8.41 x 10 6 based on the body length.The results of the investigation indicated that the body-fin combination was generally stable about the assumed moment center for the range of fin size and fin sweep angle of the tests, although at Mach number 2.00 and at a sweep angle of 65°, regions of instability were indicated for angles of attack above about 9°.The addition of the control wings had little effect on the longitudinal stability but did produce a substantial increase in normal-force curve slope and in axial force.Deflection of the control wings was effective in providing increments of side force and normal force with essentially no effect on pitching or yawing moments.The presence of wing slots, which simulated slots into which the wings fold, had no effect on the aerodynamic characteristics of the model.