WIND TUNNEL TESTS ON DREV - ISL REFERENCE MODELS AT SUPERSONIC SPEEDS (SERIES ISLFPWT-1)

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Authors
  1. Girard, B.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
In support of a cooperative research programme between the Defence Research Establishment Valcartier (DREV), Canada and the Institut franco-allemand de recherches de St-Louis (ISL), France under the auspices of "Theme 25 - Aeroballistics" of the Franco-Canadian Accord, wind tunnel tests were performed in a DREV 0.6 m x 0.6 m facility. Three models were tested at Mach numbers 2.0 to 4.0: - Cone/Cylinder with/without fins and a generic flechette (25, 30 and 35 L/D). Aerodynamic coefficients measurement tests were made for all configurations and surface pressure distribution tests were made with the Cone/Cylinder model without fins. The rationale for this test series was to compare test results with those from similar tests performed at ISL with particular attention to the influence of Reynolds number. The present memorandum which describes the experiment, is complementary to other publications that utilize data from DREV and ISL (from wind tunnel and aeroballistics range tests) to validate CFD simulations works and to perform analysis of experimental observations.
Keywords
Mach 2.0 to 4.0;Aerodynamic coefficients
Report Number
DREV-TM-9704 — Technical Memorandum
Date of publication
01 Aug 1997
Number of Pages
190
DSTKIM No
97-04097
CANDIS No
505524
Format(s):
Hardcopy;Document Image stored on Optical Disk

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