WIND-TUNNEL INVESTIGATION OF A RAM-JET CANARD MISSILE MODEL HAVING A WING AND CANARD SURFACES OF DELTA PLAN FORM WITH 70° SWEPT LEADING EDGES LONGITUDINAL AND LATERAL STABILITY AND CONTROL CHARACTERISTICS AT A MACH NUMBER OF 1.60

摘要

An investigation has been, conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the longitudinal and lateral stability and control characteristics of a ram-jet canard missile having a center-of-gravity location of -19.5 percent of the wing mean aerodynamic chord. The tests were made at a Mach number of 1.60 and a Reynolds number of 3.83 x 10° based on the Tiring mean aerodynamic chord. The model had a wing and vertical and horizontal canard surfaces of delta plan form with 70° swept leading edges. Nacelles were mounted in the vertical plane on unswept pylons near the rear of the model. The effects of vertical-canard size and nacelle longitudinal location on the stability characteristics were also investigated.nAll configurations were found to be longitudinally stable with a static margin of about 14 percent of the wing mean aerodynamic chord. A maximum trim angle of attack of 11.5° and trim lift coefficient of 0.42 was obtainable with the maximum horizontal-canard deflection of 12°.