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Experimental and Computational Results of a Maneuverable Power-Law Elliptic Cross-Section Projectile at Supersonic Speeds
Experimental and Computational Results of a Maneuverable PowerLaw Elliptic CrossSection Projectile at Supersonic Speeds Author:John J. Bertin, James R. Forsythe, Paul H. Schuricht This is a AIR FORCE RESEARCH LAB EGLIN AFB FL MUNITIONS DIRECTORATE report procured by the Pentagon and made available for public release. It has been reproduced in the best form available to the Pentagon. It is not spiral-bound, but rather assembled with Velobinding in a soft, white linen cover. The Storming Media report number is A671693. The ... more »abstract provided by the Pentagon follows: This report documents the results of an experimental and computational investigation of a power-law elliptic cross-section projectile for increased maneuverability. Surface-pressure measurements and force-and-moment measurements have been conducted in the Tri-Sonic Wind-Tunnel (TWT) at the Aerodynamic Research Center (ARC) at the U.S. Air Force Academy. Flow visualization data were also obtained in the form of Schlieren photographs and surface oil-flow patterns during these test programs. Data were obtained at a Mach number of 4.2% over a range of Reynolds numbers (based on the free-stream conditions and the model length) of 12.47 million to 19.96 million over an angle-of-attack range from -11 to +11 degrees. The data from these wind-tunnel tests were compared with computations generated using the Cobalt code, which was run on the Beowulf cluster at the High-Performance Computing Facility (HPCF) at the ARC. It should be noted that the experimental and the computational parts of this investigation were conducted concurrently in a double-blind fashion. That is, the results from the experimental effort were not used to influence the way in which the results from the CFD effort were produced and vice versa. Free flight investigations were carried out at the U.S. Air Force Research Laboratory Munitions Directorate Aeroballistic Research Facility and were conducted at Mach numbers ranging from 3.0 to 5.0. The free flight experimental data consisted of nine free-flight projectiles launched within an instrumented facility.« less