Compressible Gas Flow with Laminar Boundary Layer Passing Simple Nozzle (Part 1)

Abstract

In this report, compressible gas flow passing a long and straight simple nozzle is analysed, considering the influence of the laminor boundary layer at the wall, and its theoretical calculation with air is reported. According to its results, the state of flow is determined by the nozzle-characteristic-number shown here : and as the function of which, the distribution of the boundary layer's thickness and mainstream's pressure etc. are calculated. Especially, this report differs from the others in the important points that, when the nozzle charact. -number is more than 0.03, the throat of mainstream is calculated to be at about 80% of the nozzle length, and behind which the main stream becomes super-sonic, inspite of parallel-nozzle or pipe.