High-Speed Boundary-Layer Stability on a Cone with Localized Wall Heating or Cooling

A localized heating or cooling effect on stability of the boundary-layer flow on a sharp cone at zero angle of attack and freestream Mach number 6 is analyzed. Experiments were carried out in the Transit-M wind tunnel of the Institute of Theoretical and Applied Mechanics (Novosibirsk, Russia) for di...

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Bibliographic Details
Published in:AIAA journal 2015-09, Vol.53 (9), p.2512-2524
Main Authors: Fedorov, Alexander, Soudakov, Vitaly, Egorov, Ivan, Sidorenko, Andrey, Gromyko, Yury, Bountin, Dmitry, Polivanov, Pavel, Maslov, Anatoly
Format: Article
Language:English
Subjects:
Aerodynamics
Angle of attack
Boundaries
Boundary layer
Boundary layer flow
Computational fluid dynamics
Cooling
Cooling effects
Cooling rate
Direct numerical simulation
Flow stability
Fluid flow
Heating
Mach number
Mathematical analysis
Mathematical models
Navier-Stokes equations
Reynolds number
Stability
Stability analysis
Wind tunnels
Zero angle of attack
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Summary:A localized heating or cooling effect on stability of the boundary-layer flow on a sharp cone at zero angle of attack and freestream Mach number 6 is analyzed. Experiments were carried out in the Transit-M wind tunnel of the Institute of Theoretical and Applied Mechanics (Novosibirsk, Russia) for different heating/cooling intensities and freestream Reynolds numbers. The mean flows with localized heating/cooling are calculated using axisymmetric Navier–Stokes equations. These solutions are used for the spatial linear stability analysis to estimate the transition onset points using the eN method. Direct numerical simulations of two-dimensional disturbances propagating in the boundary layer through the cooled/heated region are performed. The experiment and computations showed similar qualitative trends. The localized cooling decreases the second-mode amplitude and delays transition. The heating produced an opposite effect, which is less pronounced.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J053666