Comparative Surface Heat Transfer Measurements in Hypervelocity  Flow

Flaherty, William; Austin, Joanna

doi:10.2514/6.2010-671

Cited by 9 publications

(8 citation statements)

References 30 publications

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“…Firstly, it is an error of a signal conversion (voltage) to the temperature because of use standard translation tables which errors may reach 1.7% change in temperature, which correspond directly to errors in the heat flow for the same 1.7%. Secondly, the accuracy of the thermophysical properties of the materials of the thermocouple junction can cause errors up to 8% of the heat flux [23,34]. Since the same type of sensors is used, the physical error sources are the same, but the values are different.…”

Section: Resultsmentioning

confidence: 99%

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Goldfeld¹,

Pickalov²

2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Section: Resultsmentioning

confidence: 99%

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Goldfeld¹,

Pickalov²

2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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“…22 For more information regarding the development, testing and performance verification of the thermocouples, see Flaherty and Austin. 23 …”

Section: Methodsmentioning

confidence: 99%

Evaluation of Hypervelocity Carbon Dioxide Blunt Body Experiments in an Expansion Tube Facility

Sharma

Swantek

Flaherty

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This work represents efforts to study high-enthalpy carbon dioxide flows in anticipation of the upcoming Mars Science Laboratory (MSL) and future missions. The current study extends the previous presentation of experimental results by the comparison now with axisymmetric simulations incorporating detailed thermochemical modeling. The work is motivated by observed anomalies between experimental and numerical studies in hypervelocity impulse facilities. In this work, experiments are conducted in the Hypervelocity Expansion Tube (HET) which, by virtue of its flow acceleration process, exhibits minimal freestream dissociation in comparison to reflected shock tunnels. This simplifies the comparison with computational result as freestream dissociation and considerable thermochemical excitation can be neglected. Shock shapes of the Laboratory aeroshell and spherical geometries are compared with numerical simulations. In an effort to address surface chemistry issues arising from high-enthalpy carbon dioxide ground-test based experiments, spherical stagnation point and aeroshell heat transfer distributions are also compared with simulation. The shock stand-off distance has been identified in the past as sensitive to the thermochemical state and as such, is used here as an experimental measureable for comparison with CFD and two different theoretical models. For low-density, small-scale experiments it is seen that models based upon assumptions of large binary scaling values are unable to match the experimental and numerical results. Very good agreement between experiment and CFD is seen for all shock shapes and heat transfer distributions fall within the non-catalytic and super-catalytic solutions.

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“…The NIST thermocouple reference tables were used to convert from voltage to temperature. 19 The method of heat transfer deconvolution is described in Flaherty and Austin, 20 and is based on the work of Sanderson. 16 Four different models were used in for these experiment: a flat plate, a linear ramp, and two curved ramp models.…”

Section: Methodsmentioning

confidence: 99%

Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers

Flaherty

Austin

2010

40th Fluid Dynamics Conference and Exhibit

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Heat transfer measurements are made to investigate the effects of concave surface curvature on a high-stagnation enthalpy boundary layer in a Mach 5.1 flow. Experiments are carried out using two curved models with 16 and 25 degree turning angles, and baseline planar models (flat plate and linear ramp) for comparative study. Streamwise and spanwise cross-sections are obtained. Significant destabilization of the boundary layer is observed over the adverse pressure gradient geometries. For the curved surfaces, the heat flux distribution appears to exhibit a quadratic dependence with streamwise distance, in contrast with the linear dependence observed on the linear ramp.

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Comparative Surface Heat Transfer Measurements in Hypervelocity Flow

Cited by 9 publications

References 30 publications

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Evaluation of Hypervelocity Carbon Dioxide Blunt Body Experiments in an Expansion Tube Facility

Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers

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