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Nosetip Bluntness Effects on Transition at Hypersonic Speeds: Experimental and Numerical AnalysisThe existing database of transition measurements in hypersonic ground facilities has established that the onset of boundary layer transition over a circular cone at zero angle of attack shifts downstream as the nosetip bluntness is increased with respect to a sharp cone. However, this trend is reversed at sufficiently large values of the nosetip Reynolds number, so that the transition onset location eventually moves upstream with a further increase in nosetip bluntness. This transition reversal phenomenon, which cannot be explained on the basis of linear stability theory, was the focus of a collaborative investigation under the NATO STO group AVT-240 on Hypersonic Boundary-Layer Transition Prediction. The current paper provides an overview of that effort, which included wind tunnel measurements in three different facilities and theoretical analysis related to modal and nonmodal amplification of boundary layer disturbances. Because neither first and second-mode waves nor entropy-layer instabilities are found to be substantially amplified to initiate transition at large bluntness values, transient (i.e., nonmodal) disturbance growth has been investigated as the potential basis for a physics based model for the transition reversal phenomenon. Results of the transient growth analysis indicate that stationary disturbances that are initiated within the nosetip or in the vicinity of the juncture between the nosetip and the frustum can undergo relatively significant nonmodal amplification and that the maximum energy gain increases nonlinearly with the nose radius of the cone. This finding does not provide a definitive link between transient growth and the onset of transition, but it is qualitatively consistent with the experimental observations that frustum transition during the reversal regime was highly sensitive to wall roughness, and furthermore, was dominated by disturbances that originated near the nosetip. Furthermore, the present analysis shows significant nonmodal growth of traveling disturbances that peak within the entropy layer and could also play a role in the transition reversal phenomenon.
Document ID
20190028399
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
External Source(s)
Authors
Pedro Paredes ORCID
(National Institute of Aerospace Hampton, Virginia, United States)
Meelan M Choudhari ORCID
(Langley Research Center Hampton, Virginia, United States)
Fei Li
(Langley Research Center Hampton, Virginia, United States)
Joseph S Jewell ORCID
(United States Air Force Research Laboratory Wright-Patterson AFB, Ohio, United States)
Roger L Kimmel
(United States Air Force Research Laboratory Wright-Patterson AFB, Ohio, United States)
Eric C Marineau
(Arnold Engineering Development Complex Silver Spring, Maryland, United States)
Guillaume Grossir
(Von Karman Institute for Fluid Dynamics Sint-Genesius-Rode, Belgium)
Date Acquired
August 1, 2019
Publication Date
November 30, 2018
Publication Information
Publication: Journal of Spacecraft and Rockets (JSR)
Publisher: American Institute of Aeronautics and Astronautics
Volume: 56
Issue: 2
Issue Publication Date: March 1, 2019
ISSN: 0022-4650
e-ISSN: 1533-6794
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-29701
Report Number: NF1676L-29701
Funding Number(s)
WBS: 109492.02.07.01.01
PROJECT: ARMD_109492
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Keywords
Freestream Mach Number
Laminar turbulent transition
Angle of attack
Entropy
Hypervelocity wind tunnels
Hypersonic speed
Vehicle technology
Arnold Engineering Development Complex
Kinetic energy
Parabolized stability equations
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