Performance Study for Guidance of a Generic Missile Using Flow Effectors on the Nose
Abstract
Because of the high costs associated with flight and experimental measurements in wind tunnels and test cells, Computational Fluid Dynamics (CFD) is becoming a useful tool for predicting fluid flow. With the recent performance improvements of computers and numerical codes, a much faster prediction of fluid flow, shock wave position and aerodynamic coefficients calculation is believed to be possible allowing the simulations of more complex flow. This report lies in the continuity of exploring phases on the feasibility to use Flow effectors for Active Flow Control for the Guidance of Missiles. The present study is done on an aerodynamic geometry with a conical nose adapted to the wind tunnel model. Different combinations of rectangular flow effectors place on the nose can have very different characteristics in steady and unsteady operation. Each one of these items has a direct impact on the general performance of the missile. The missile performances can also be affected by flight parameters such as Mach number, altitude and angle of attack. The aim of this study is to evaluate the performance of an active flow control in the form of a rectangular flow disturber with the aim of controlling a missile. Using CFD, combinations of different dimensions of flow effectors at different positions on the surface of the missile were evaluated for their impact on overall system performance for a missile flying at Mach 1.5 at an altitude of 6 km from zero to twenty degrees of angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2004
- Accession Number
- ADA637776
Entities
People
- P. Gosselin
- P. Rainville