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Supersonic jet and crossflow interaction: Computational modeling

 Supersonic aircraft and crossflow interaction: Computational modeling Dissertation

Progress in Aerospace Sciences 57 (2013) 1–24

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Progress in Aerospace Sciences

journal home page: www.elsevier.com/locate/paerosci

Supersonic jet and crossflow interaction: Computational building Ez Hassan a, d, John Jatte b, Hikaru Aono c, Douglas Davis d, Wei Shyy a, e, n a

Office of Aerospace Engineering, College or university of Michigan, Ann Arbor, MI, UNITED STATES Taitech, Inc., Beavercreek, WOW, USA

Japan Aerospace Pursuit Agency (JAXA), Sagamihara, The japanese d

Usaf Research Clinical, Fairborn, WOW, USA

elizabeth

The Hk University of Science and Technology, Kowloon, Hong Kong w

c

a r t i c l elizabeth i in f um

abstract

Available on the web 9 August 2012

The supersonic jet-in-crossflow problem that involves shocks, thrashing mixing, and large-scale vortical structures, needs special treatment for turbulent flow to obtain correct solutions. Different turbulence building techniques are reviewed and compared with regards to their performance in forecasting results consistent with the experimental info. Reynolds-averaged Navier–Stokes (RANS) types are limited in prediction of gas structure because of their inability to accurately get unsteadiness inside the flow. Significant eddy simulation (LES) is usually not yet functional due to really large main grid requirement close to the wall. Cross RANS/LES may offer reasonable compromise between reliability and efficiency. The cross models derive from various strategies such as direct blending of RANS and LES, separate eddy ruse (DES), and filter-based multi-scale models. Particularly, they can be utilized to evaluate the thrashing Schmidt number modeling techniques used in jet-in-crossflow simulations. Specifically, an adaptive approach may be devised by utilizing the information obtained from the settled field to assist assign the value of turbulent Schmidt number in the sub-filter field. The adaptive approach combined with multi-scale model improves the results especially when highly refined grids will be needed to deal with small structures involved in the mixing process. & 2012 Elsevier Ltd. Most rights set aside.

Keywords:

Plane and crossflow interactions

Supersonic flows

Computational modeling

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Introduction........................................................................................................ a couple of Experimental attempts................................................................................................. 2 RANS and LES....................................................................................................... 4 Hybrid RANS/LES: building........................................................................................... 5 four. 1 .

Direct hybrid model: Boles et al. [50]............................................................................. six 4. 2 .

Detached turn simulation (DES) [47, 43, 80]#@@#@!!......................................................................... six 4. 2 . 1 .

Peterson and Candler [71] software to supersonic crossflow................................................... several 4. 3.

Filter primarily based approach (Multi-scale model).......................................................................... 7 4. a few. 1 .

Hassan et al. [52, 72] Multi-scale style.............................

References: Expo. 2000: Munich, Germany.

Electronic. Hassan ainsi que al. / Progress in Aerospace Savoir 57 (2013) 1–24

[39] Lin K-C, Ryan M, Carter C, Gruber Meters, Raffoul C

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