OH PLIF visualization of the UVa supersonic combustion experiment: configuration A

Hydroxyl radical (OH) planar laser-induced fluorescence (PLIF) visualizations were performed in the University of Virginia supersonic combustion experiment. The test section was set up in configuration A, which includes a Mach 2 nozzle, combustor, and extender section. Hydrogen fuel was injected through an unswept compression ramp at two different equivalence ratios. Through the translation of the optical system and the use of two separate camera views, the entire optically accessible range of the combustor was imaged. Single-shot, average, and standard deviation images of the OH PLIF signal are presented at several streamwise locations. The results show the development of a highly turbulent flame structure and provide an experimental database to be used for numerical model assessment.Graphical Abstract

[1]  G. Laufer,et al.  KrF laser-induced OH fluorescence imaging in a supersonic combustion tunnel , 1992 .

[2]  Ronald K. Hanson,et al.  Spatially Resolved Water Measurements in a Scramjet Combustor Using Diode Laser Absorption , 2014 .

[3]  Ronald S. Fry,et al.  A Century of Ramjet Propulsion Technology Evolution , 2004 .

[4]  R. Hanson,et al.  Comparison of excitation techniques for quantitative fluorescence imaging of reacting flows , 1993 .

[5]  S. Bakhrakh,et al.  Experimental and Numerical Study , 2005 .

[6]  C. Goyne,et al.  Seeding Bias in Particle Image Velocimetry Applied to Dual-Mode Scramjet , 2015 .

[7]  Adrian Tatnall,et al.  Spacecraft system engineering , 2011 .

[8]  William H. Heiser,et al.  Hypersonic Airbreathing Propulsion , 1994 .

[9]  Christopher P. Goyne,et al.  Experimental and numerical study of a dual-mode scramjet combustor , 2006 .

[10]  Luca M. L. Cantu,et al.  Image Analysis of Hydroxyl-Radical Planar Laser-Induced Fluorescence in Turbulent Supersonic Combustion , 2016 .

[11]  Paul M. Danehy,et al.  Fluorescence imaging and streakline visualization of hypersonic flow over rapid prototype wind-tunnel models , 2008 .

[12]  Roland H. Krauss,et al.  Laser selection criteria for OH fluorescence measurements in supersonic combustion test facilities , 1993 .

[13]  Daniel B. Le,et al.  Shock Train Leading-Edge Detection in a Dual-Mode Scramjet , 2008 .

[14]  Randall T. Voland,et al.  X-43A Hypersonic vehicle technology development , 2006 .

[15]  Hassan Hassan,et al.  Large-Eddy / Reynolds-Averaged Navier-Stokes Simulations of a Dual-Mode Scramjet Combustor , 2012 .

[16]  Michael K. Smart,et al.  Flight Data Analysis of the HyShot 2 Scramjet Flight Experiment , 2006 .

[17]  Charles R. McClinton,et al.  X-43 Hypersonic Vehicle Technology Development , 2005 .

[18]  Christopher P. Goyne,et al.  Dual-Pump CARS Measurements in the University of Virginia's Dual-Mode Scramjet: Configuration "C" , 2012 .

[20]  E. T. Curran,et al.  Scramjet Engines: The First Forty Years , 2001 .

[21]  Christopher P. Goyne,et al.  Demonstration of Capability of Water Flux Measurement in a Scramjet Combustor using Tunable Diode Laser Absorption Tomography and Stereoscopic PIV , 2011 .

[22]  J. Hank,et al.  The X-51A Scramjet Engine Flight Demonstration Program , 2008 .

[23]  G. Laufer,et al.  Planar OH density and apparent temperature measurements in a supersonic combusting flow , 1995 .

[24]  OH PLIF Visualization of the UVa Supersonic Combustion Experiment: Configuration A , 2012 .

[25]  Michael Unser,et al.  Elastic registration of biological images using vector-spline regularization , 2005, IEEE Transactions on Biomedical Engineering.

[26]  Ian A. Schultz,et al.  Tunable Diode Laser Absorption Sensor for Measurements of Temperature and Water Concentration in Supersonic Flows , 2011 .

[27]  Russell R. Boyce,et al.  OH PLIF Imaging of Supersonic Combustion using Cavity Injection , 2005 .

[29]  Con J. Doolan,et al.  Comparison of Hydrogen and Hydrocarbon-Fueled Scramjet Engines for Orbital Insertion , 2007 .