English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

This paper describes the numerical simulation of the NASA Langley ResearchCenter supersonic H2 -Air combustion chamber performed using two approaches tomodel the presumed probability density function (PDF) in the flamelet progressvariable (FPV) framework. The first one is a standard FPV model, builtpresuming the functional shape of the PDFs of the mixture fraction, Z, and ofthe progress parameter, {\Lambda}. In order to enhance the predictioncapabilities of such a model in high-speed reacting flows, a second approach isproposed employing the statistically most likely distribution (SMLD) techcniqueto presume the joint PDF of Z and {\Lambda}, without any assumption about theirbehaviour. The standard and FPV-SMLD models have been developed using the lowMach number assumption. In both cases, the temperature is evaluated by solvingthe total-energy conservation equation, providing a more suitable approach forthe simulation of supersonic combustion. By comparison with experimental data,the proposed SMLD model is shown to provide a clear improvement with respect tothe standard FPV model, especially in the auto-ignition and stabilizationregions of the flame.

Computing supersonic non-premixed turbulent combustion by an SMLD flamelet progress variable model