Wind tunnel validation of computational fluid dynamics-based aero-optics model

Abstract A computational fluid dynamics (CFD)-based aero-optics validation study was conducted in wind tunnel tests at the US Air Force Academy. A 12 in diameter hemisphere-on-cylinder laser turret was tested in the 3 ft×3 ft subsonic wind tunnel at flow speeds ranging from mach 0.3 to 0.5. Flow val...

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Bibliographic Details
Published in:Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2009-06, Vol.223 (4), p.393-406
Main Authors: Nahrstedt, D, Hsia, Y-C, Jumper, E, Gordeyev, S, Ceniceros, J, Weaver, L, DeSandre, L, McLaughlin, T
Format: Article
Language:English
Subjects:
Aero-optics
Aerodynamics
Aerospace industry
Aircraft components
Computational fluid dynamics
Correlation analysis
Cylinders
Dimensional measurement
Fluid dynamics
Fluid flow
Inflow
Lasers
Line of sight
Mathematical models
Navier-Stokes equations
Pressure
Separation
Subsonic aircraft
Testing
Turbulence models
Turret
Two-equation turbulence model
Variance
Wind tunnel testing
Wind tunnels
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Summary:Abstract A computational fluid dynamics (CFD)-based aero-optics validation study was conducted in wind tunnel tests at the US Air Force Academy. A 12 in diameter hemisphere-on-cylinder laser turret was tested in the 3 ft×3 ft subsonic wind tunnel at flow speeds ranging from mach 0.3 to 0.5. Flow validation was based on mean and rms velocity, mean pressure profile, rms unsteady pressure, and separation point. Optical validation was based on rms phase variance and inflow phase correlation length derived from two-dimensional Hartmann wavefront sensor data, measured over a 5 in beam. The CFD code used a two-equation turbulence model with partially-averaged Navier—Stokes approach. Good agreement was observed between measurements and predictions over line-of-sight angles ranging from 60 to 132° measured with respect to flow heading.
ISSN:0954-4100
2041-3025
DOI:10.1243/09544100JAERO385