Numerical predictions of the Mars Science Laboratory reaction control system jets interacting with a Mach 10 hypersonic flow are compared to experimental nitric oxide planar laser-induced fluorescence data. The steady Reynolds-averaged Navier–Stokes equations using the Baldwin–Barth one-equation turbulence model were solved using the OVERFLOW code. The experimental fluorescence data used for comparison consist of qualitative two-dimensional visualization images, qualitative reconstructed three-dimensional flow structures, and quantitative two-dimensional distributions of streamwise velocity. Through modeling of the fluorescence signal equation, computational flow images were produced and directly compared to the qualitative fluorescence data. Post processing of the experimental and simulation data enabled the jet trajectory to be extracted for a more quantitative comparison. The two-dimensional velocity fields were reconstructed through interpolation of a series of single-component velocity profiles. Each distribution of single-component velocity was obtained using molecular tagging velocimetry. After validating the numerical model, the numerical solution was further examined to gain insight into hypersonic jet-in-crossflow interaction. Novel nitric oxide planar laser induced fluorescence experiments are proposed based on this analysis.
Mars Science Laboratory Reaction Control System Jet Computations with Visualization and Velocimetry
Journal of Spacecraft and Rockets ; 50 , 6 ; 1183-1195
2013-07-24
13 pages
Article (Journal)
Electronic Resource
English
Mars Science Laboratory Reaction Control System Jet Computations with Visualization and Velocimetry
Online Contents | 2013
|Comparison of MSL RCS Jet Computations with Flow Visualization and Velocimetry
British Library Conference Proceedings | 2012
|PLIF STUDY OF MARS SCIENCE LABORATORY CAPSULE REACTION CONTROL SYSTEM JETS
British Library Conference Proceedings | 2011
|