Aeroballistic Range and Wind Tunnel Tests of the Basic Finner Reference Projectile from Subsonic to High Supersonic Velocities

PDF

Authors
  1. Dupuis, A.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN)
Abstract
Free-flight tests were conducted in the Defence R&D Canada (DRDC) Valcartier aeroballistic range and wind tunnel experiments in the DRDC-Valcartier Indraft Trisonic wind tunnel on the Basic Finner reference projectile at subsonic, transonic and supersonic velocities. The projectile consisted of four rectangular fins on a cone-cylinder body with a total length-to-diameter ratio of 10.0. The fins were canted at 2.0 degrees. The Mach number range tested was from 0.5 to 4.5. All the main aerodynamic coefficients and stability derivatives were well determined from the free-flight tests. The wind tunnel results consisted of the usual static aerodynamic coefficients. The angles of attack were varied from -10 degrees to + 10.0 degrees and the model was tested at a roll orientation of 0.0 degrees and 45.0 degrees. The wind tunnel aerodynamic coefficients are compared with the free-flight absolute-determined data.

Il y a un résumé en français ici.

Keywords
MLM (Maximum Likelihood Method);6DOF (Six degrees of freedom);Aeroballistic range tests;Aerodynamic coefficients;Finned projectiles;Flight dynamics;Gun launched;Linear theory;MLM Methodology;Subsonic;Transonic
Report Number
DRDC-VALCARTIER-TM-2002-136 — Technical Memorandum
Date of publication
01 Oct 2002
Number of Pages
85
DSTKIM No
CA021322
CANDIS No
518050
Format(s):
Hardcopy;Document Image stored on Optical Disk

Permanent link

Document 1 of 1

Date modified: