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  • 1
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    Review of Fluorescence-Based Velocimetry Techniques to Study High-Speed Compressible Flows (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper reviews five laser-induced fluorescence-based velocimetry techniques that have been used to study high-speed compressible flows at NASA Langley Research Center. The techniques discussed in this paper include nitric oxide (NO) molecular tagging velocimetry (MTV), nitrogen dioxide photodissociation (NO2-to-NO) MTV, and NO and atomic oxygen (O-atom) Doppler-shift-based velocimetry. Measurements of both single-component and two-component velocity have been performed using these techniques. This paper details the specific application and experiment for which each technique has been used, the facility in which the experiment was performed, the experimental setup, sample results, and a discussion of the lessons learned from each experiment.
    Keywords: Aeronautics (General)
    Type: AIAA Paper 2013-0339 , NF1676L-14797 , 51st AIAA Aerospace Sciences Meeting; Jan 07, 2013 - Jan 10, 2013; Grapevine, TX; United States
    Format: application/pdf
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  • 2
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    Coherent Anti-Stokes Raman Spectroscopy (CARS) Measurements in Supersonic Combustors at NASA Langley Research Center (2005)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This paper describes the recent use of coherent anti-Stokes Raman spectroscopy (CARS) to study supersonic combustion at NASA Langley Research Center. CARS is a nonlinear optical measurement technique used to measure temperature and species mole fractions remotely in harsh environments. A CARS system has been applied to two different combustor geometries at NASA Langley. Both experiments used the same vitiated wind-tunnel facility to create an air flow that simulates flight at Mach numbers of 6 and 7 for the combustor inlet and both experiments used hydrogen fuel. In the first experiment, the hydrogen was injected supersonically at a 30-degree angle with respect to the incoming flow. In the second experiment, the hydrogen was injected sonically at normal incidence. While these injection schemes produced significantly different flow features, the CARS method provided mean temperature, N2, O2 and H2 maps at multiple downstream locations for both. The primary aim of these measurements was to provide detailed flowfield information for computational fluid dynamics (CFD) code validation.
    Keywords: Research and Support Facilities (Air)
    Type: JANNAF 40th Combustion/28th Airbreathing Propulsion/22nd Propulsion Systems Hazards/4th Modeling and Simulation Joint Subcommittee Meeting; Jun 13, 2005 - Jun 17, 2005; Charleston, SC; United States
    Format: application/pdf
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  • 3
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    PLIF Imaging of Capsule RCS Jets, Shear Layers, and Simulated Forebody Ablation (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Planar laser-induced fluorescence (PLIF) has been used to investigate hypersonic flows associated with capsule reentry vehicles. These flows included reaction control system (RCS) jets, shear layer flow, and simulated forebody heatshield ablation. Pitch, roll, and yaw RCS jets were studied. PLIF obtained planar slices in these flowfields. These slices could be viewed individually or they could be combined using computer visualization techniques to reconstruct the three dimensional shape of the flow. The tests described herein were conducted in the 31-Inch Mach 10 Air Tunnel at NASA Langley Research Center. Improvements to many facets of the imaging system increased the efficiency and quality of both data acquisition, in addition to increasing the overall robustness of the system.
    Keywords: Aeronautics (General)
    Type: 46th AIAA Aerospace Sciences Meeting and Exhibit; Jan 07, 2008 - Jan 10, 2008; Reno, NV; United States
    Format: application/pdf
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  • 4
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    Fluorescence Imaging of Rotational and Vibrational Temperature in a Shock Tunnel Nozzle Flow (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Two-dimensional rotational and vibrational temperature measurements were made at the nozzle exit of a free-piston shock tunnel using planar laser-induced fluorescence. The Mach 7 flow consisted predominantly of nitrogen with a trace quantity of nitric oxide. Nitric oxide was employed as the probe species and was excited at 225 nm. Nonuniformities in the distribution of nitric oxide in the test gas were observed and were concluded to be due to contamination of the test gas by driver gas or cold test gas.The nozzle-exit rotational temperature was measured and is in reasonable agreement with computational modeling. Nonlinearities in the detection system were responsible for systematic errors in the measurements. The vibrational temperature was measured to be constant with distance from the nozzle exit, indicating it had frozen during the nozzle expansion.
    Keywords: Research and Support Facilities (Air)
    Type: AIAA Paper 98-2703 , AIAA Journal; 41; 9; 1722-1732|20th AIAA Advanced Measurement and Ground Testing Technology Conference; Jun 15, 2001 - Jun 18, 2001; Albuquerque, NM; United States
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