Wind Tunnel Tests on DREV - ISL Reference Afterbodies at Mach 2.0 (Series ISLPWT-2)

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Authors
  1. Girard, B.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
In support to a co-operative 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 the DREV 0.6 m x 0.6 m facility at a Mach number of 2.0 with two configurations of afterbody models of reference: Cylinder with/without fins based on the Southhampton University Calibration Body. Boundary layer characterization tests were performed with a smooth afterbody model without fins and surface pressure distribution surveys were made with afterbody models with and without fins. The rationale for this test series was to compare test results with those from similar tests performed at ISL in test conditions that differ to some extent. This memorandum describes the experiment and is complementary to other DREV and ISL publications on wind tunnel and aeroballistic range tests and on CFD simulations.
Keywords
Flight dynamics
Report Number
DREV-TM-1999-134 — Technical Memorandum
Date of publication
06 Mar 2000
Number of Pages
201
DSTKIM No
CA001291
CANDIS No
513130
Format(s):
Hardcopy;Document Image stored on Optical Disk

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