Theory of Stagnation Point Heat Transfer in Dissociated Air

Fay, James A.; Riddell, Frederick R.

doi:10.2514/8.7517

Cited by 802 publications

(443 citation statements)

References 5 publications

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“…Overall, a total combined uncertainty of ±10 % is estimated, including a ±5 % uncertainty in the calibration of the thermal properties of the gauges ( ρc p k) g , a ±2 % in the calibration of resistivity α R and system error of 3 % (input voltage, measurement resolution angain calibration). Validation based on the measurement of stagnation heat transfer on a 5-mm-radius hemispherical nose finds a repeatability of q o,N = 132.6 W/cm 2 ± 1.3 % , with similarly good agreement with theory (Fay and Riddell 1958), thus corroborating the conservative measure of the specified uncertainties (note uncertainties in Table 1 are effectively systematic).…”

Section: Methodssupporting

confidence: 49%

“…With this in mind, the complete q ′ max dataset is first evaluated against the well-established hypersonic stagnation heat transfer relations deriving from the work of Fay and Riddell (1958) and Kemp et al (1959). For 2D configurations, and based on the peak heating at R 1 over tall cylindrical obstacles, Crabtree et al (1970) bring forward the following relation:…”

Section: Stagnation Heatingmentioning

confidence: 99%

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Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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Section: Methodssupporting

confidence: 49%

Section: Stagnation Heatingmentioning

confidence: 99%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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“…The heat §uxes obtained in the experiments are nondimensionalized by q 0 ratabled using the Fay£s and Riddell£s formula for the critical point on sphere [19]. Under the conditions of UT-1 wind tunnel (in presence of moisture, dust in free stream, and other reasons), the actual heat §ux on the model can exceed this value.…”

Section: Resultsmentioning

confidence: 99%

Tangential injection to a supersonic flow on a blunted nose

Chuvakhov

Егоров

Ezhov

et al. 2017

Progress in Flight Physics

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The §ow pattern and the heat §ux to a body surface at a tangential gas injecting have been investigated. The cooling air was injected to a §ow through the tangential axisymmetric slot on the spherically blunted cylinder. The experiments were conducted at M ∞ = 6, Re ∞,Rw = 0.76 · 10 6 , angle of attack α = 0 • 30 • , and the slot width h k /R w = 0 0.021. The mass rate of the injecting gas was G * = g j /(πρ ∞ u 2 ∞w ) = 0 0.16. It has been shown that maximum of the heat §ux toward the sphere surface can be su©ciently decreased. Numerical investigations have been carried out using the solution of the Navier Stokes equations for axisymmetric two-dimensional (2D) viscous compressible unsteady §ows at α = 0.

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“…The heat flux is calculated integrating the time evolution of the temperature measured by a Medtherm coaxial thermocouple (type K) that is flush mounted at the stagnation point. Then the heat flux is converted to the total enthalpy of the flow using semi-empirical correlations based on the similarity solution of the boundary layer, as proposed by Fay and Riddell [28] or by Sutton and Graves [29]. The accuracy expected for this kind of measurements is estimated to be approximately 15%.…”

Section: Sensors and Probesmentioning

confidence: 99%

Development and testing of the ACT-1 experimental facility for hypersonic combustion research

Baccarella

Liu

Passaro

et al. 2016

Meas. Sci. Technol.

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PAPERDevelopment and testing of the ACT-1 experimental facility for hypersonic combustion research Manuscript version: Accepted Manuscript Accepted Manuscript is "the version of the article accepted for publication including all changes made as a result of the peer review process, and which may also include the addition to the article by IOP Publishing of a header, an article ID, a cover sheet and/or an 'Accepted Manuscript' watermark, but excluding any other editing, typesetting or other changes made by IOP Publishing and/or its licensors" This Accepted Manuscript is © © 2016 IOP Publishing Ltd.During the embargo period (the 12 month period from the publication of the Version of Record of this article), the Accepted Manuscript is fully protected by copyright and cannot be reused or reposted elsewhere. As the Version of Record of this article is going to be / has been published on a subscription basis, this Accepted Manuscript is available for reuse under a CC BY-NC-ND 3.0 licence after the 12 month embargo period.After the embargo period, everyone is permitted to use copy and redistribute this article for non-commercial purposes only, provided that they adhere to all the terms of the licence https://creativecommons.org/licences/by-nc-nd/3.0 Although reasonable endeavours have been taken to obtain all necessary permissions from third parties to include their copyrighted content within this article, their full citation and copyright line may not be present in this Accepted Manuscript version. Before using any content from this article, please refer to the Version of Record on IOPscience once published for full citation and copyright details, as permissions will likely be required. All third party content is fully copyright protected, unless specifically stated otherwise in the figure caption in the Version of Record.View the article online for updates and enhancements. Abstract.A new pulsed-arc-heated hypersonic wind tunnel facility, designated as ACT-1 (Arc-heated Combustion Test-rig 1), has been developed and built at the University of Notre Dame in collaboration with the University of Illinois at Urbana-Champaign and Alta S.p.A. The aim of the design is to provide a suitable test platform for experimental studies on supersonic and hypersonic turbulent combustion phenomena. ACT-1 is composed of a high temperature gas-generator system and a model scramjet combustor that is installed in an open-type vacuum test section of the wind tunnel facility. The gasgenerator is designed to produce high-enthalpy (stagnation temperature = 2,000 K -3,500 K) hypersonic flows for a run time up to 1 second. The supersonic combustor section is composed of a compression ramp (scramjet inlet), an internal flow channel of constant cross-section, a fuel jet nozzle, and a flame holder (wall cavity). The facility allows three-way optical accesses (top and sides) into the supersonic combustor to enable various advanced optical and laser diagnostics. In particular, planar laser Rayleigh scattering (PLRS), high-speed schlieren imaging and...

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Theory of Stagnation Point Heat Transfer in Dissociated Air

Cited by 802 publications

References 5 publications

Reattachment heating upstream of short compression ramps in hypersonic flow

Reattachment heating upstream of short compression ramps in hypersonic flow

Tangential injection to a supersonic flow on a blunted nose

Development and testing of the ACT-1 experimental facility for hypersonic combustion research

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