SUPERSONIC INVESTIGATION OF A SPINNING AND NONSPINNING MODEL OF A CAJUN (OR APACHE) ROCKET VEHICLE WITH ROLL-CONTROL TABS

摘要

A model of the Cajun rocket with nose cone and standard fin assembly (scaled to 0.401) was tested in the Langley Unitary Plan wind tunnel from Mach numbers of 2.30 to 4.63 at a Reynolds number of 2.5 × 106 per foot. Some additional data are presented for Reynolds number of 4.0 × 106 per foot and for model incidence angles other than zero. Measured wind-tunnel results on 11 roll-control-tab configurations (plates with wedge-shaped cross section) for mounting on the trailing edge of the stabilizing fins of Cajun stage to obtain roll-effectiveness data are presented herein along with the general aerodynamic characteristics defining this vehicle. The data obtained for the total rolling-moment coefficient and the damping-in-roll derivative compared favorably with theoretical results.