Accession Number : AD0893814
Title : Wind Tunnel and Flight Test Stability and Control Derivatives for the X-24A Lifting Body.
Descriptive Note : Final rept. 17 Apr 69-4 Jun 71,
Corporate Author : AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
Personal Author(s) : Kirsten, Paul W.
Report Date : APR 1972
Pagination or Media Count : 170
Abstract : The objectives of determining the stability and control derivatives of the X-24A lifting body from flight test data and correlating these results with predictions were successfully accomplished. Stability and control derivatives were extracted from flight data using a digital-analog computer matching program. Although the accuracy of results varied for individual derivatives and test maneuvers, the overall quality of test results from the matching program was felt to be quite good. The Mach number and angle of attack ranges investigated were approximately 0.4 to 1.6 and 0 to 20 degrees, respectively. Differences between the flight-derived values and wind tunnel and theoretically predicted values of several derivatives were found throughout the flight envelope. Some of these differences were of sufficient magnitude to significantly alter the predicted handling of qualities of the vehicle. In addition, large discrepancies from wind tunnel predictions were discovered in the static directional stability derivative at supersonic Mach numbers and high angles of attack. These decrepancies were attributed to aerodynamic power effects from the rocket engine. (Author)
Descriptors : (*LIFTING REENTRY VEHICLES, FLIGHT TESTING), MODEL TESTS, STABILITY, CONTROL, MATHEMATICAL PREDICTION, CORRELATION TECHNIQUES, COMPUTER PROGRAMS, DIGITAL COMPUTERS, ANALOG COMPUTERS, MACH NUMBER, ANGLE OF ATTACK, WIND TUNNEL MODELS, MANEUVERABILITY, AERODYNAMIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, YAW, MATHEMATICAL ANALYSIS, PITCH(MOTION), ROLL, WEIGHT, MOMENT OF INERTIA, SIDESLIP.
Subject Categories : Aerodynamics
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE