FREE-FLIGHT INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A 10-DEG SEMIANGLE CONE AT MACH NUMBERS FROM 6 TO 16
Final rept. May 1967-Jun 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A 1000-ft hypervelocity range was used to obtain the free-flight static and dynamic stability and drag data presented for a 10-deg semiangle cone. Measurements indicate that the damping-in-pitch derivatives for the cone increase appreciably with increasing Mach number between M 8 and 16 at a Reynolds number based on model length and free-stream conditions of about 400, 000. Further, the pitching-moment derivative for the cone decreases significantly as the nose-radius to base-radius ratio of the cone is increased up to 0.1 for amplitudes greater than about 5 deg. Comparisons of the range stability data with wind tunnel data involving sting-supported models obtained in different test facilities indicate that appreciable differences in the pitching-moment derivative and the damping-in-pitch derivatives exist in some cases.
- Fluid Mechanics