Aeroballistic range tests of the Air Force Finner reference projectile

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Authors
  1. Dupuis, A.D.
  2. Hathaway, W.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN);Arrow Tech Associates, South Burlington VT (US)
Abstract
Free-flight tests were conducted in the Defence R&D Canada Valcartier (DRDC-V) aeroballistic range on the Air Force Finner reference projectile from subsonic to supersonic velocities. The projectile consisted of four clipped delta fins on a tangent ogive cylinder body with a total length-to-diameter ratio of 10.0. Fin cants of 0 degree, 2 degrees and 4 degrees were imposed. The mach number range tested was between 0.5 and 2.5. All the main aerodynamic coefficients and stability derivatives were determined by using linear theory, six-degree-of-freedom single- and multiple-fit reductions techniques. The results were also compared with those from another aeroballistic range.

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Keywords
Aeroballistic range tests;Aerodynamic coefficients;Flight dynamics;Linear theory;MLM (Maximum Likelihood Method);MLM Methodology;6DOF (Six degrees of freedom)
Report Number
DRDC-VALCARTIER-TM-2002-008 — Technical Memorandum
Date of publication
08 May 2002
Number of Pages
79
DSTKIM No
CA020769
CANDIS No
517505
Format(s):
Hardcopy;Document Image stored on Optical Disk

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