WIND TUNNEL TESTS ON SABOT SEPARATION OF BASIC PROJECTILE CONFIGURATIONS (SERIES SABOTFPWT-1)

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Authors
  1. Girard, B.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
In support of a co-operative research work between DREV and countries of the TTCP program (WTP-2 Panel) to study the flight dynamics of sabot separation, supersonic wind tunnel test series were performed in DREV's (0.6 m x 0.6 m) indraft facility in order to obtain experimental data on surface static pressure distribution and aerodynamic stability coefficients. By assuming small flow time scale, in flight relative attude and locations of sabots/projectile system are frozen in the test section at some instant of the separation process. The complete test setting consisted of a projectile and three sabot petals. This memorandum describes the wind tunnel tests performed with full-scale models of C-76 projectile/sabots and with generic cone/cylinder projectile/sabots. A total of 483 runs were made at Mach numbers between 3.50 and 3.99, for a variety of roll angles and angles of attack up to 25 deg. Equations used for treatment of data are presented together with test conditions and a summary of the results. Also, a description of instrumentation test setting and several model drawings were incorporated. Win tunnel results compared rather well with the DREV (CFD) simulations.
Keywords
Aeroballistic range tests;Chocked flow;Finned projectiles;Flight dynamics;Roll damping fins;Sabot separation;Aeroballistics
Report Number
DREV-TM-9741 — Technical Memorandum
Date of publication
01 Jun 1998
Number of Pages
260
DSTKIM No
98-01495
CANDIS No
508325
Format(s):
Hardcopy;Document Image stored on Optical Disk

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