Boundary-Layer Stability Analysis for Stetson’s Mach 6 Blunt-Cone Experiments

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Boundary-Layer Stability Analysis for Stetson’s Mach 6 Blunt-Cone Experiments

Boundary-Layer Stability Analysis for Stetson’s Mach 6 Blunt-Cone Experiments

Jewell, Joseph S. / Kimmel, Roger L.

The results of a seminal experimental study of the effects of bluntness and swallowing length on transition on an 8 deg cone at zero angle of attack in Mach 6 high-Reynolds-number flow are analyzed with the STABL-2D computational fluid dynamics code package. Mean flow solutions and parabolized stability analyses for a total of 11 different nose-tip bluntnesses, ranging from sharp to a 15.24 mm radius, are obtained. For the sharpest cases, the $N$ factor at transition is approximately seven; but, as bluntness increases and the calculated swallowing distance lengthens, the computed $N$ factor at the experimentally observed transition location drops below the level at which Mack’s second mode would be expected to lead to transition. These results indicate that the dominant instability mechanism for the bluntest cases is not the second mode, and oblique mode analysis also excludes these modes as the dominant instability mechanism.

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Title :

Boundary-Layer Stability Analysis for Stetson’s Mach 6 Blunt-Cone Experiments

Contributors:

Jewell, Joseph S. (author) / Kimmel, Roger L. (author)

Published in:

Journal of Spacecraft and Rockets ; 54 , 1 ; 258-265

Publication date :

2016-10-18

Size :

8 pages

ISSN :

0022-4650 , 1533-6794

DOI :

https://doi.org/10.2514/1.A33619

Type of media :

Article (Journal)

Type of material :

Electronic Resource

Language :

English

Keywords :

Laminar Turbulent Transition , Reynolds Number , Angle of Attack , Computational Fluid Dynamics Code , Stagnation Pressure , Parabolized Stability Equations , Air Force Research Laboratory , Hypersonic Wind Tunnels , Heat Transfer , Finite Volume Formulation

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