Abstract
A rotating cone is used as a model of a swept wing in supersonic flow. The correlation of transition location (N=9) with non-dimensional parameters describing the crossflow profile is discussed. Transition location does not correlate with the traditional definition of crossflow Reynolds number. A new parameter that appears to correlate for adiabatic-wall boundary-layer flow on rotating cones at low supersonic Mach numbers has been found. Also, an increase of stagnation temperature is found to be only slightly stabilizing.
This work was supported by the Air Force Office of Scientific Research under Contract No. F49620-88-C-0076 and NASA/Ames Research Center under the Graduate Student Researchers Program.
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Reed, H.L., Haynes, T.S. (1993). Observations in Using Linear Stability Theory for 3-D Supersonic Boundary Layers. 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_12
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