Boundary Layer survey on a Model of a Sparrow AIM-7M Missile in the DREV Trisonic Wind Tunnel

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Authors
  1. Fournier, E.Y.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
The present wind tunnel investigation is part of a project studying the effectiveness of reaction jet controls on missiles and projectiles. As a comparison basis between reaction jets and conventional control appendages was required, a complete database of aerodynamic coefficients and pressure surveys had to be developed on a specific model shape. It was decided to use a model of the Sparrow AIM-7M medium range missile for this purpose as it would also demonstrate the capability of DREV's trisonic wind tunnel in the experimental investigation of actual missiles. Measurement of the boundary layer characteristics in the vicinity of a control wing and of a stability fin were performed in order to compare the body interaction on fins with respect to that of the full scale vehicle. A successful comparison with analytical results for free-flight conditions should allow for good correlation between free-flight and wind tunnel aerodynamic coefficients. The database for the reaction jet project was generated and comparative results have indicated that DREV's trisonic wind tunnel can generate good technical results for missile shaped models.
Keywords
Aerodynamic coefficients;Pressure surveys;Sparrow AIM 7M;AIM-7 missile
Report Number
DREV-TM-1999-088 — Technical Memorandum
Date of publication
01 Dec 1999
Number of Pages
30
DSTKIM No
CA000334
CANDIS No
512346
Format(s):
Hardcopy;Document Image stored on Optical Disk

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