Aerodynamic Coefficients Measurement on a Model of a Sparrow Aim-7M Missile in the DREV Trisonic Wind Tunnel


  1. Founier, E.Y.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
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 had to be developed on a generic model shape. However, instead of using a generic model, it was decided to use a model of the Sparrow AIM-7M medium range missle in an effort to demonstrate the capability of DREV's wind tunnel in the experimental investigation of actual missiles, and also due to th elarge aerodynamic database existing on this vehicle. Testing covered a large range of Mach numbers, from 1.5 to 4.0, and angles of incidence from -10 degrees to + 10 degrees. Two different roll orientations of the model were studied (0 degree and 45 degrees). Additionally, data involving wing deflections were also generated for the same Mach number range, over the same model incidence range, for deflection angles up to 20 degrees. A build-up component method was used during the testing phase: data for a clean body (F1), for a body with tail fins only (f3), for a body with control wings only (F2), for a body with both sets of appendages (F4), and finally, for a body with both sets of appendages and antennas and attachment pins (F5) were generated. TRUNCATED
AIM-7 missiles;Aerodynamic coefficients
Report Number
DREV-TM-1999-050 — Technical Memorandum
Date of publication
01 Jul 1999
Number of Pages
Hardcopy;Document Image stored on Optical Disk

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