A COMPARISON OF TWO TECHNIQUES UTILIZING ROCKET-PROPELLED VEHICLES FOR THE DETERMINATION OF THE DAMPING-IN-ROLL DERIVATIVE

摘要

Rocket-powered flight investigations have been conducted for the purpose of comparing damping-in-roll results as obtained from a torque-nozzle technique in which the test configuration is the complete vehicle, and the sting-mount technique in which the test configuration is mounted on a nose sting on the rocket-powered vehicle. The Mach number range of these tests was approximately 0.6 to 1.4 corresponding to Reynolds num¬ber ranges of about 1 x 106 to 2.2 x 106 for the sting-mount technique, and about 2.3 X 106 to 8.0 X 106 for the torque-nozzle technique. Good agreement of the damping-in-roll derivative was obtained between the two techniques for a configuration consisting of a pointed cylindrical body having three rectangular unswept wings of NACA 65A009 airfoil sections.