Quiet Tunnel Measurements of HIFiRE-5 Boundary-Layer Transition

The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratory and Australian Defence Science and Technology Organisation. The principal goal of HIFiRE flight five is to measure hypersonic boundary-layer...

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Bibliographic Details
Published in:AIAA journal 2015-04, Vol.53 (4), p.832-846
Main Authors: Juliano, Thomas J, Borg, Matthew P, Schneider, Steven P
Format: Article
Language:English
Subjects:
Aerodynamics
Angle of attack
Boundaries
Boundary layer transition
Cross flow
Defense programs
Experimentation
Flight tests
Fluid dynamics
Fluid flow
Ground tests
Heat flux
Heat transfer
High Reynolds number
Hypersonic flight
Hypersonic flow
Leading edges
Low noise
Noise levels
Noise reduction
Reynolds number
Temperature-sensitive paints
Three dimensional bodies
Tunnels (transportation)
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Summary:The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratory and Australian Defence Science and Technology Organisation. The principal goal of HIFiRE flight five is to measure hypersonic boundary-layer transition on a three-dimensional body. The HIFiRE flight tests are supported by a ground test campaign; this paper presents measurements of heat flux and boundary-layer transition in the Boeing/AFOSR Mach-6 Quiet Tunnel. This facility has been developed to provide quiet flow at high Reynolds number, with low noise levels comparable to flight. This tunnel’s good optical access enabled global measurement of the heat flux by means of temperature-sensitive paint. Two modes of transition were observed: transition along the centerline, suspected to arise from the amplification of second-mode waves in the boundary layer, and transition roughly halfway between the centerline and leading edges, probably due to the breakdown of crossflow vortices. Reducing the noise level from conventional to quiet substantially delayed both transition modes. Increasing the angle of attack from 0 to 4 deg delayed the crossflow transition mode on the windward side. Transition moved forward as freestream unit Reynolds number increased from 2.6·106/m to 11.9·106/m.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J053189