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X. Zhong (1998)
DIRECT NUMERICAL SIMULATION OF 3-D HYPERSONIC BOUNDARY LAYER RECEPTIVITY TO FREESTREAM DISTURBANCES
J. Schmisseur, S. Schneider, S. Collicott (1998)
Receptivity of the Mach-4 boundary layer on an elliptic cone to laser-generated localized freestream perturbations
D. Bushnell (1990)
Notes on Initial Disturbance Fields for the Transition Problem
S. Schneider (2001)
Hypersonic Laminar Instability on Round Cones Near Zero Angle of Attack
A. Smits, K. Hayakawa, K. Muck (1983)
Constant temperature hot-wire anemometer practice in supersonic flowsExperiments in Fluids, 1
J. Schmisseur, S. Collicott, S. Schneider (2000)
Laser-Generated Localized Freestream Perturbations in Supersonic and Hypersonic FlowsAIAA Journal, 38
S. Barre, D. Alem, J. Bonnet (1995)
Experimental study of a normal shock/homogeneous turbulence interactionAIAA Journal, 34
Y. Zel’dovich, Y. Raizer, W. Hayes, R. Probstein, S. Gill (2002)
Physics of Shock Waves and High-Temperature Hydrodynamic Phenomena
S. Schneider, C. Haven (1995)
Quiet-flow Ludwieg tube for high-speed transition researchAIAA Journal, 33
E. Spina, C. Mcginley (1994)
Constant-temperature anemometry in hypersonic flow: critical issues and Sample resultsExperiments in Fluids, 17
J. Schmisseur (1997)
Receptivity of the boundary layer on a Mach-4 elliptic cone to laser-generated localized freestream perturbations
M. Hussaini, G. Erlebacher (1999)
Interaction of an Entropy Spot with a ShockAIAA Journal, 37
G. Doggett, N. Chokani, S. Wilkinson (1997)
Effect of angle of attack on hypersonic boundary-layer stabilityAIAA Journal, 35
P. Duck, D. Lasseigne, M. Hussaini (1997)
The Effect of Three-Dimensional Freestream Disturbances on the Supersonic Flow Past a Wedge.Physics of Fluids, 9
S. Kline (1953)
Describing Uncertainties in Single-Sample ExperimentsMechanical Engineering, 75
Controlled, localized disturbances were introduced into the supersonic freestream upstream of a 4:1 elliptic cross-section cone. The response of the initially laminar boundary layer to the laser-generated freestream perturbation was measured above the cone minor axis. The experiment was conducted in the Mach-4 Purdue Quiet-flow Ludwieg tube at a freestream unit Reynolds number of 4.5 million/m. The focused beam from a frequency-doubled Nd:YAG laser was used to generate the disturbance. The perturbation existed in the flowfield as a region of locally heated air, referred to here as the thermal spot. Constant-temperature anemometry was used to characterize the boundary-layer response to the introduction of the thermal spot. The response was largest and most complex near the boundary-layer edge. The duration of the measured boundary-layer response was an order of magnitude greater than the measured duration of the disturbance in the freestream. Within the boundary layer, the mass-flux deviation introduced by the thermal spot was of the same magnitude as the local mean mass flux. The optically generated disturbance is potentially useful as a perturbation source in future boundary-layer receptivity experiments.
Experiments in Fluids – Springer Journals
Published: Aug 1, 2002
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