23 Dec

Shock Wave / Laminar Boundary Layer Interaction with Real-gas Effects Presented at AIAA Aviation 2014

Experimental studies have been conducted in the LENS-XX expansion tunnel facility to generate datasets for shock wave / laminar boundary layer interactions at flight-duplicated conditions. These cases are at high enthalpy conditions where laminar separated regions are influenced by thermal and chemical excitation.  Detailed surface heat transfer and pressure measurements have been measured for 25O/55O double cone and a 30O hollow cylinder flare configurations for a range of freestreram velocities from 3 km/s to 6.5 km/s.  Details of the model configurations and the freestream conditions at which these studies have been conducted, together with earlier measurements and measurements upstream of the interaction regions were presented to enable computations to be performed with both Navier-Stokes and DSMC prediction methods for “blind comparisons” with the experimental data.  Details of the experiment, the comparisons with state-of-the-art CFD codes, and tabulations of the data are given below.


Presentation and Datasets:

Experimental Overview and CFD Comparison Presentation
Double Cone Dataset
Hollow Cylinder Flare Dataset
Experimental Overview Paper

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