Inhibition of Flow Separation at High Speed: Calculation of nonadiabatic laminar boundary layers on conical compression surfaces. Volume IV

Frederick K. Goodwin · Larry L. Lynes

Jan 1969 · Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force

About this ebook

This is the last part of a four-part series of reports describing an investigation of the inhibition of boundary-layer separation of the free-interaction type at high speeds through the use of surface cooling. The purpose of this report is to extend the other work of the authors to configurations representative of axisymmetric compression spikes. The analysis is developed and a computer program written for a spike which consists of a conical nose on which separation occurs followed by compression surface. No data were found to compare with the theory. A calculation made with the pressure gradient prescribed by the body shape rather than by free interaction is compared with experiment. The comparisons, which were made for skin friction, heat transfer, and pressure distributions, were good. The significant effect of wall cooling in delaying separation for the prescribed pressure gradient case is shown. It is also shown that a free-interaction solution can be joined to a prescribed pressure gradient solution so that the solution will go smoothly through separation to reattachment.