Temperature Measurements in a Hypersonic Boundary Layer Using Planar Laser-Induced Fluorescence

Palma, P. C.; Mallinson, S. G.; O’Byrne, Sean; Danehy, Paul M.; Hillier, R.

doi:10.2514/2.1172

Cited by 14 publications

(1 citation statement)

References 7 publications

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“…These probes have clear-cut disadvantages, such as disturbing the flow, slow response time, susceptibility to damage in a harsh environment, a limited temperature range and single point measurement. As a consequence, several non-invasive optical methods, such as emission spectroscopy [8] and planar laser-induced fluorescence (PLIF) [9,10], have been developed lately to tackle these shortcomings.…”

Section: Introductionmentioning

confidence: 99%

Time-resolved temperature characterization of a hypersonic shock layer using a single high-speed color camera for aerospace design applications

Deep¹,

Krishna²,

Jagadeesh³

2019

Meas. Sci. Technol.

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Two-color ratio pyrometry (TCRP) using a high-speed color camera has been used for temperature characterization of a hypersonic shock layer. The camera, used as a pyrometer, was calibrated in-house using a monochromator to determine its spectral responsivity and was used to acquire time-resolved images of the flow field over test models at a frame rate of 20 000 fps to understand the evolution of temperature inside the shock region. The optical efficiency of the monochromator and other optical equipment were determined separately and corrected for. Two test models, a flat-faced cylinder of diameter 70 mm and a hemisphere of diameter 80 mm, were used for the experiments to study the effect of geometry on the results. Experiments were performed in a free-piston-driven shock tunnel at a stagnation enthalpy of 5.2 MJ kg−1. The average steady-state temperature in the stagnation region in the cylinder was about 3650 K ± 3% (uncertainty in the shock layer due to camera noise), and for the hemisphere it was 3300 K ± 6%. The resolved temperature was 14% higher than that obtained from a similar, but time-integrated, measurement obtained using a digital single lens reflex (DSLR) camera. Steady 2D numerical simulations were performed to reconstruct the 3D flow assuming azimuthal symmetry, and an algorithm was developed to use the shape of the temperature profile along the line-of-sight (LOS) derived from simulations to predict the actual stagnation-plane temperature from the experimental LOS-integrated TCRP-derived temperature. The actual temperature in the stagnation region on the vertical plane of symmetry (stagnation plane) for the cylinder and the hemisphere were higher by 2.76% and 1.77%, respectively, than the corresponding TCRP-derived LOS-integrated temperature. The results are promising for future use in determining intense temperature gradients and heat flux in the vicinity of space vehicles and for the design of efficient thermal protection systems.

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Section: Introductionmentioning

confidence: 99%

Time-resolved temperature characterization of a hypersonic shock layer using a single high-speed color camera for aerospace design applications

Deep¹,

Krishna²,

Jagadeesh³

2019

Meas. Sci. Technol.

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Evaluation of nitric oxide laser-induced fluorescence thermometry techniques in a hypersonic boundary layer

et al. 2020

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Plif temperature and velocity distributions in laminar hypersonic flat-plate flow

O’Byrne

Danehy

Houwing

20th International Congress on Instrumentation in Aerospace Simulation Facilities, 2003. ICIASF '03.

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Rotational temperature and velocity distributions have been measured across a hypersonic laminar flat-plate boundary layer, using planar laser-induced fluorescence. The measurements are compared to a finite-volume computation and a first-order boundary layer computation, assuming local similarity. Both computations produced similar temperature distributions and nearly identical velocity distributions. The disagreement between calculations is ascribed to the similarity solution not accounting for leading-edge displacement effects. The velocity measurements agreed to within the measurement uncertainty of 2 % with both calculated distributions. The peak measured temperature was 200 K lower than the computed values. This discrepancy is tentatively ascribed to vibrational relaxation in the boundary layer.

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Temperature Measurements in a Hypersonic Boundary Layer Using Planar Laser-Induced Fluorescence

Cited by 14 publications

References 7 publications

Time-resolved temperature characterization of a hypersonic shock layer using a single high-speed color camera for aerospace design applications

Time-resolved temperature characterization of a hypersonic shock layer using a single high-speed color camera for aerospace design applications

Evaluation of nitric oxide laser-induced fluorescence thermometry techniques in a hypersonic boundary layer

Plif temperature and velocity distributions in laminar hypersonic flat-plate flow

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