Wind tunnel tests with a spinning model of a 5-calibre Army-Navy spinner at Mach 0.5 to 3.0

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Authors
  1. Girard, B.
  2. Drouin, G.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
Most of shells and bullets that are fired from a gun barrel have to be gyroscopically stabilized during flight by a high spin rate (axial) and this must be made in conjunction with a proper ratio of their axial and lateral inertia moments. For the wind tunnel tests related to spin stabilized projectiles, it is very desirable to be able to spin the model which makes possible to evaluate the aerodynamic effects induced by the spinning motion as the Magnus forces and moments, the spin/roll damping and also to study the influence of the spin rate on other aerodynamic coefficients (lift, drag, pitching moment, etc...) When considering the relatively small size of the test section, an electrical motor was used for the spin rig. It is a departure from the more current air turbine state-of-the-art but has proven to be efficient with the DREV facility. This memorandum describes wind tunnel tests made in the DREV 0.6 m x 0.6 m trisonic wind tunnel with a spinning model of an ARMY-NAVY SPINNER 5-calibre. This is a standard model configuration used to qualify and normalize wind tunnel test results. These tests were primordially intended to measure the spin damping and the Magnus force and also the influence of the spin rate on other standard aerodynamic coefficients, in order to evaluate the results that can be obtained with a spin rig apparatus and its controller developed at DREV. TRUNCATED

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Keywords
Aerodynamic coefficients;Flight dynamics;Roll damping;Spin damping
Report Number
DREV-TN-2001-116 — Technical Note
Date of publication
01 Sep 2001
Number of Pages
251
DSTKIM No
CA011574
CANDIS No
516137
Format(s):
Hardcopy;Document Image stored on Optical Disk

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