Interaction between Shock Wave and Boundary Layer in Nonequilibrium Hypersonic Rarefied Flow

Abstract

An experimental study of the interaction between a shock wave and a boundary layer over a flat plate with a sharp leading edge in hypersonic rarefied gas flow is presented. Experiments in a low-density wind tunnel using an electron beam probe were conducted at the Shock Wave Laboratory, RWTH Aachen, Germany. Rotational temperatures for stagnation temperatures of T 0 = 670∼1 000 K and Kn = 0.024∼0.028 based on a reference length of 0.05 m were calculated using Muntz's method and Robben and Talbot's method. The domain of quasi two-dimensional flow over the plate was determined from three-dimensional rotational temperature measurements. Nonequilibrium between translational and rotational temperatures was observed near the leading edge, and the experimental rotational relaxation length explains the rotational collision number of 2∼4.

DSMC Simulation of Non-uniform Flow Effects behind a Conical Nozzle

“…Tokumasu and Matsumoto presented the DMC (Dynamic Molecular Collision) model to simulate such a flow, and they showed the agreement between the numerical and the experimental results for one-dimensional shock wave [4]. The authors also simulated a flow around a flat plate with a sharp leading edge by using the collision model [5,6,7].…”

Monte Carlo Simulation of Hypersonic Rarefied Gas Flow using Rotationally and Vibrationally Inelastic Cross Section Models

“…In the present study, the function for the rotationally inelastic collision cross section of the SICS model, parameters for the vibrationally inelastic collision probability of the VICS model, and the probability density function for deflection angle were defined from transport coefficients, rotational collision number, and vibrational relaxation time of nitrogen gas. The validity of the present cross section model was examined by applying it to the simulation of hypersonic rarefied gas flow around a flat plate and comparing the results with experimental data 12 .…”

Planar Laser Induced Iodine Fluorescence for the Investigation of the Aerodynamics of Reaction Control System Jets on Mars-Entry Aeroshells

“…Optical conditions [21]. The Electron Beam Fluorescence technique, which is a quantitative technique that analyzes resulting fluorescence from an excitation electron beam source, is a technique primarily used in rarefied gas flow investigations [22][23][24][25]. However, this technique is limited only to low density (rarefied) flows due to problems with beam scattering, quenching and the beam current measurement at higher densities [22].…”