Abstract
The effect of wall cooling on the instability of a two-dimensional, flat-plate supersonic boundary layer under stratospheric flight conditions at Mach number 3 is calculated using both the inviscid and viscous linear stability theories. At any fixed Reynolds number, cooling stabilizes the first mode and destabilizes the second and higher modes. Transition is estimated on the basis of an envelope N-factor obtained from the separate N-factors of each normal mode. At this Mach number, the second-mode is a remaining source of instability after a certain amount of wall cooling has stabilized the first mode. If transition is initiated by linear instability, a transition reversal must take place, but at high Reynolds numbers and frequencies. If the transition Reynolds number is increased by active cooling or some other means, it is possible for the laminar flow to be maintained by the cooling available from thermal radiation alone.
The work described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration (NASA). Support from the Aerodynamics Division of the Office of Aeronautics and Exploration Technology, NASA, is gratefully acknowledged.
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Mack, L.M. (1993). Effect of Cooling on Boundary-Layer Stability at Mach Number 3. In: Ashpis, D.E., Gatski, T.B., Hirsh, R. (eds) Instabilities and Turbulence in Engineering Flows. Fluid Mechanics and Its Applications, vol 16. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-1743-2_9
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