Hypersonic boundary layers

S. M. Scala and G. W. Sutton, The Two-Phase Hypersonic Boundary Layer— A Study of Surface Melting, 1958 Heat Transfer and Fluid Mechanics Institute. Stanford Stanford University Press, 1958, 231-240. 

Multiplexed diode laser sensors have also been applied for measurements of gas temperature, velocity, and H2O partial pressures in hypervelocity air flows at the Calspan University of Buffalo Research Center s (CUBRC) Large Energy National Shock Tunnel (LENS Tunnel) in Buffalo, New York [12]. The sensors were developed to provide quantitative characterization of the facility operation and, in particular, the freestream flow properties as a function of time. The measurements were recorded using a hardened probe, which contained critical optical components and photodetectors, that was installed directly into the hypersonic shock-tunnel near the nozzle exit to minimize complications due to boundary layers and facility vibration. 

Brooks, S. B M. J. Lewis, and R. R. Dickerson, Nitric Oxide Emissions from the High-Temperature Viscous Boundary Layers of Hypersonic Aircraft within the Stratosphere, J. Geophys. Res., 98, 16755-16760 (1993). 

E. J. Hopkins, M. W. Rubesin, M. Inouye, E. R. Keener, G. G. Mateer, and T. E. Polek, Summary and Correlation of Skin-Friction and Heat-Transfer Data for a Hypersonic Turbulent Boundary Layer on Simple Shapes, NASA Tech. Note D-5089, 1969. 

---