Supersonic Combustion Experiments for CFD Model Development and Validation (Invited)

Cutler, Andrew D.; Danehy, Paul M.; O’Byrne, Sean; Rodríguez, Cristian; Drummond, J. P.

doi:10.2514/6.2004-266

Cited by 17 publications

(17 citation statements)

References 15 publications

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“…The simplest of such estimate is given by the relative difference e ¼ ðf 1 À f 1 Þ= f 1 [33], where, f represent any quantity of interest and the indices 1 and 2 refer to the fine and coarse grid solution respectively. (In the present calculation, the centerline pressure is taken as the parameter of interest) Roache [34] has proposed a grid-convergence index (GCI) as an error based on uncertainty estimate of the numerical solution as,…”

Section: Results and Discussion Grid Independence Studymentioning

confidence: 99%

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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In the present study, the turbulent structure of coaxial supersonic H 2 -air jet is explored numerically by solving three dimensional RANS equations along with two equation k-e turbulence model. Grid independence of the solution is demonstrated by estimating the error distribution using Grid Convergence Index. Distributions of flow parameters in different planes are analyzed to explain the mixing and combustion characteristics of high speed coaxial jets. The flow field is seen mostly diffusive in nature and hydrogen diffusion is confined to core region of the jet. Both single step laminar finite rate chemistry and turbulent reacting calculation employing EDM combustion model are performed to find the effect of turbulencechemistry interaction in the flow field. Laminar reaction predicts higher H 2 mol fraction compared to turbulent reaction because of lower reaction rate caused by turbulence chemistry interaction. Profiles of major species and temperature match well with experimental data at different axial locations; although, the computed profiles show a narrower shape in the far field region. These results demonstrate that standard two equation class turbulence model with single step kinetics based turbulence chemistry interaction can describe H 2 -air reaction adequately in high speed flows.

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Section: Results and Discussion Grid Independence Studymentioning

confidence: 99%

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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“…As mentioned, previous smaller scale designs resulted in very complex nonlinear response surfaces 3,4 . Because of the need for a much higher fidelity model over the larger design regions and the ability to possibly fit piecewise polynomial models in smaller design regions, it was decided that nested FCCD designs would be implemented.…”

Section: Data Collectionmentioning

confidence: 99%

“…Three examples can be found in Parker et al 1 , Danehy et al 2 , and Cutler et al 3 . The paper by Parker et al 1 describes a number of statistical techniques and how they are employed over different areas of the hypersonic research project.…”

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confidence: 99%

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Design strategies for response surface models for the study of supersonic combustion

Johnson

Parker

Montgomery

et al. 2008

Quality & Reliability Eng

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An application of a classical design approach to an experiment involving the study of supersonic combustion is described in this paper. The case study described is that of an experiment whose objective is to create response surfaces of the mean and variance of several flow parameters as a function of location within a supersonic jet flow field. The approach demonstrated in this paper involves the use of a classic response surface methodology design in a unique manner. Additionally a unique application involving the sub-sampling and replication strategies is developed in a similar manner to those of robust parameter design. The sub-sampling and replication techniques allow for the ability to systematically account for the precision in mean and variance models of the output response variables. The final design prescribed met the experimental objectives of the project by creating the ability to fit response surfaces and allowing for the experimenters to understand the relative precision of their estimates based on the final sub-sampling and replication techniques. Results from one section of the region of interest are used to illustrate two different modeling approaches. The performance of both modeling approaches in prediction of new data is illustrated. The conclusions also include a discussion of the future work that will follow.

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“…Efforts have continued to conduct well instrumented experimentation of scramjet combustor flow field to validate CFD data. The SCHolAR experiment conducted at NASA langley's Direct Connect Supersonic Test facilities [21][22] gives detailed measurements of temperatures and species mass fraction at various cross sections as well as wall pressures for hydrogen fuel is injected at 30° angle to Mach 2 airstreams with 1200 K temperature in a divergent duct. The schematic of the experimental condition is shown in Fig.…”

Section: Hydrogen Fuelled Scramjet Combustor With Wall Injectionmentioning

confidence: 99%

A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

et al. 2016

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Accurate prediction of surface temperature of high speed aerospace vehicle is very necessary for the selection of material and determination of wall thickness. For aerothermal characterisation of any high speed vehicle in its full trajectory, it requires number of detailed computational fluid dynamics (CFD) calculations with different isothermal calculations. From the detailed CFD calculations for different flow conditions and geometries, it is observed that heat transfer coefficients scale with the difference of adiabatic wall temperature and skin temperature. A simple 'isothermal method', is proposed to calculate heat flux data with only two CFD simulations one on adiabatic condition and other on isothermal condition. The proposed methodology is validated for number of high speed test cases involving external aerodynamic heating as well as high speed combusting flow. The computed heat fluxes and surface temperatures matches well with experimental and flight measured values.

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Supersonic Combustion Experiments for CFD Model Development and Validation (Invited)

Cited by 17 publications

References 15 publications

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Design strategies for response surface models for the study of supersonic combustion

A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

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