AEROBALLISTIC RANGE TESTS OF THE BASIC FINNER REFERENCE PROJECTILE AT SUPERSONIC VELOCITIES

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Authors
  1. Dupuis, A.D.
  2. Hathaway, W.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
Free-flight tests were conducted in the Defence Research Establishment Valcartier (DREV) Aeroballistic Range on the Basic Finner reference projectile from transonic to high supersonic velocities. The projectile consisted of four rectangular fins on a cone-cylinder body with a total length-to-diameter ratio of 10.0 Fin cants of 0 degree, 2 degree and 4 degree were imposed. The Mach number range tested was between 1.0 and 4.5. All the main aerodynamic coefficients and stability derivatives were well determined using linear theory, six-degree-of-freedom single- and multiple-fit reductions techniques. The results were also compared with results from other aeroballistic ranges. The fins on the models fired at Mach 4.5 abalted during flight. A dynamic stability analysis showed a Magnus instability at certain Mach numbers and spin rates.
Keywords
Basic finner;Flight dynamics;Magnus instability;Maximum Likelihood Estimation;Stability analysis;Linear theory
Report Number
DREV-TM-9703 — Technical Memorandum
Date of publication
01 Aug 1997
Number of Pages
140
DSTKIM No
97-04096
CANDIS No
505377
Format(s):
Hardcopy;Document Image stored on Optical Disk

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