A re-examination of self-simialr solution possibilities for steady laminar boundary layers is given for non-adiabatic hypersonic flows of an ideal gas. Two apparently new such solutions are found, pertaining to adverse pressure gradients, both of which involve no separation with distance into the pressure rise. The first involves an exponential pressure rise on a cooled similarly-shaped body, while the second involves a modified ramp-type pressure rise. The skin frictio, heat transfer, displacement thickness and weak viscous interactioninduced pressure change properties of these two solution families are analysed in detail, including their application to high speed inlet type of flows.
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