868 research outputs found
The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations
Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models
The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag
Flight tests at transonic and supersonic speeds of an airplane-like configuration with thin straight sharp-edge wings and tail surfaces
Determination of Longitudinal Stability and Control Characteristics from Free-Flight Model Tests with Results at Transonic Speeds for Three Airplane Configurations
A test technique and data analysis method has been developed for determining the longitudinal aerodynamic characteristics from free-flight tests of rocket-propelled models. The technique makes use of accelerometers and an angle-of-attack indicator to permit instantaneous measurements of lift, drag, and pitching moments. The data, obtained during transient oscillations resulting from control-surface disturbances, are analyzed by essentially nonlinear direct methods (such as cross plots of the variation of lift coefficient with angle of attack) and by linear indirect methods by using the equations of motion for a transient oscillation. The analysis procedure has been set forth in some detail and the feasibility of the method has been demonstrated by data measured through the transonic speed range on several airplane configurations. It was shown that the flight conditions and dynamic similitude factors for the tests described were reasonably close to typical full-scale airplane conditions
Investigation of the Lateral Stability Characteristics of the Douglas X-3 Configuration at Mach Numbers from 0.6 to 1.1 by Means of a Rocket-propelled Model
Free-flight Investigation of the Control Effectiveness of a Differentially Deflected Horizontal Tail at Mach Numbers from 0.8 to 1.6
An investigation of the longitudinal characteristics of the X-3 configuration using rocket-propelled models : preliminary results at Mach numbers from 0.65 to 1.25
Rocket-model investigation of longitudinal stability and drag characteristics of an airplane configuration having a 60 degree delta wing and a high unswept horizontal tail
Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds
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