| Popis: |
The amount of cooling required to stabilize completely the laminar boundary layer on a flat plate at supersonic speeds with zero pressure gradient is calculated using the Lees-Lin theory. I t is found that, above about Mach Number 9, it is impossible to stabilize the layer with any amount of cooling when a Prandtl Number of 0.75 and the Sutherland viscosity-temperature law are assumed. The distribution of mean properties across the boundary layer are obtained by the Crocco method. The inviscid, as well as viscous, solutions are determined. Use of the stability results in missile aerodynamic heating analysis is illustrated by means of V-2 flight-temperature data. |
