FORCE BALANCE DETERMINATION OF INLET PERFORMANCE FOR ADVANCED VEHICLE APPLICATIONS TO ORBITAL VELOCITIES USING INTERNAL DRAG MEASUREMENTS

摘要

This paper presents the original work of the author, directed at the problem of deter-mining the performance levels of supersonic/hypersonic combustion inlet models. Previous approaches to this problem are discussed and a method involving force balance determination of the internal drag is proposed. Results of a computational procedure formulated for calculating inlet performance levels from measured internal drag values are presented. Effects of chemical reactions and exit flow profile no uniformity are accounted for. Levels of anticipated accuracy, using this technique, are shown to be adequate for present applications over a Mach number range of 8 to 25.