A presentation of certain numerical solutions to laminar-boundary-layer similarity equations that illustrate such previously uninvestigated areas as the effect of variable viscosity in the boundary layer and the effect of the viscous-dissipation term. Conclusions show that design parameters such as skin-friction and heat-transfer coefficients and boundary-layer thickness are sensitive to viscosity representation and Prandtl number. Also presented are some simple formulas that may be applicable to a large number of hypersonic solutions.
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