Analytical Method of Evaluating Nonuniformities in Shock Tube Flows: Application

Shock tube experiments are a primary means of obtaining ground test data for the hypersonic regime. Accurate characterization gas is crucial to understanding experimental results. However, flows produced behind shock wave has historically proven challenging. This paper applies methodology calculate shocked properties using experimentally recovered speed profile. Static pressure, pitot and heat transfer predictions found closely match range trajectories with both argon air gases. Thermochemical variations in gases depend strongly on along tube. It shown that requires accommodating influence effects associated varying speed. Tube diameter time significantly interaction variable speed, also magnitude nonuniformities gas. Location number timing stations facilities play vital role ability accurately characterize given experiment.