Performance Study for Guidance of a Missile Using Flow Effectors at Different Roll Angle Positions

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Authors
  1. Rainville, P-A.
  2. Gosselin, P.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN);Numerica Technologies Inc, Quebec City (QUE)
Abstract
This project was part of DRDC technology investment found (TIF) project “Supersonic Missile Flight Control by Manipulation of the Flow Structure using Micro-Actuated Surfaces”. The objective was to evaluate the performance of an active flow control in the form of a rectangular flow effectors and knife-edge flow effectors with the aim of controlling a missile. Flow effectors at different roll angle positions on the surface of the missile nose were evaluated numerically for their impact on overall system performance for a missile flying at angles of attack from five to twenty degrees. A series of CFD analyses were carried out on an aerodynamic geometry with two different shapes of flow effectors. For the knife-edge flow effectors, five roll angle positions were analyzed. Seven roll angle positions with one rectangular flow effector and three roll angle positions with three rectangular flow effector were analysed. The experience gained during previous work was used as a guideline for determining the meshing strategy to be adopted, the turbulence model to be used with the correct near wall model with a Y+ around 1. From the gained experience, the mesh should be very fine and structured near the wall with a smooth mesh variation in the vortex perturbed region. The more accurate turbulence model was the realizable k-epsilon. The calculations showed that a good side force generation was possible for one flow effector at roll angle position between 225 degrees and 270 degrees. Th

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Report Number
DRDC-VALCARTIER-CR-2004-460 — Contractor Report
Date of publication
01 Dec 2004
Number of Pages
81
DSTKIM No
CA025857
CANDIS No
523588
Format(s):
Document Image stored on Optical Disk

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