Temperature Measurements of the CAN5 Projectile at Hypersonic Velocities from Free-Flight Tests

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Authors
  1. Dupuis, A.
  2. Edwards, J.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN)
Abstract
Free-flight tests were conducted at long ranges on an instrumented hypersonic projectile to study its aeroheating aspects and aerodynamic characteristics. The muzzle velocities ranged from 1880 m/s (Mach 5.4) to 2050 m/s (Mach 6.3). The projectile configuration consisted of a conical nose followed by a conical mid-body with 8 rectangular fins on a cylindrical aft end. The temperatures were measured in flight at 16 different places on the models. All the projectiles were soft recovered to collect the data. Quantitative and qualitative data were obtained on the shape of the ablated fins, the material loss and their effect on the drag coefficient.

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Keywords
Aeroheating;Temperature;Hypersonic;Free-flight tests;Ablation;Aerodynamic drag;Thermocouple;High acceleration;Sabot design;On board instrumentation;Data logger;Mach 7;Soft recovery
Report Number
DRDC-VALCARTIER-TM-2003-022 — Technical Memorandum
Date of publication
09 May 2003
Number of Pages
72
DSTKIM No
CA022499
CANDIS No
519422
Format(s):
Hardcopy;Document Image stored on Optical Disk

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