Impact of Nose-Mounted Micro-Structures on the Aerodynamics of a Generic Missile

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Authors
  1. Corriveau, D.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN)
Abstract
The need for compact and lightweight missiles combined with the requirement for high maneuverability has led over the last few years to experimentations with nonconventional means of generating aerodynamic control forces. Among the different techniques investigated, the use of micro-structures mounted on the missile forebody in order to modify the vortex structure has received some attention for low subsonic flow regime. However, very little work has been performed to demonstrate the feasibility of this concept at supersonic speed. The current experimental study proposes to look at the merit of using such micro-structures to control the aerodynamic side forces on a generic missile configuration, primarily at supersonic free stream flow conditions. The baseline experimental model used consists of a finless missile with a conical nose and an aspect ratio (L/D) of 13. Rectangular flow effectors located at two axial locations along the nose are used to distort the flow locally and hence affect the flow structure downstream. Tests were performed in the DRDC indraft wind tunnel at a free stream Mach number of 1.5 and for angles of attack varying between 0.0° and 20°. Several configurations of the nose-mounted flow effectors were investigated. The results show that a peak in the side force generated is attained between angles of attack of 15.0° and 20.0°. Furthermore, it was found that the peak side force is higher when the flow effectors are located closer to the nose tip. By i

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Keywords
EXPERIMENTAL;FLIGHT DYNAMICS;SIDE FORCE;VORTEX;MICRO-STRUCTURE;MEMS
Report Number
DRDC-VALCARTIER-TM-2004-310 — Technical Memorandum
Date of publication
01 May 2005
Number of Pages
76
DSTKIM No
CA025847
CANDIS No
523583
Format(s):
Hardcopy;CD ROM

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