Grid-free CFD turbulent wake

Earlier published engineering notes

Particulate phases for both the compressible and incompressible modules of CATAPULT are modeled as a nonequilibrium continuum.

This is in contrast to other multiphase flow codes which model particulates in a Lagrangian manner which requires tracking individual particles and can become very computationally expensive for certain problems.

Flow fields involving multiple phases are encountered in a wide variety of applications, e.g., the dynamics of atmospheric pollutants, mixing in combustion chambers, particulate flows in liquids, and cloud-rise phenomena arising from explosions.

Solutions for much of the cloud-rise research conducted in the past were often obtained using hydrocodes that solved the governing equations for compressible flow.

Measurements named in the library

Wakes can affect transition and separation in the boundary layer in three ways.

First, the FSTI rises during a wake passage compared to the between-wake value.

The calmed flow is nonturbulent, but unlike a steady nonturbulent flow, it can be very resistant to separation.

Finally, independent of the FSTI ef- fect, each wake includes a mean velocity deficit, resulting in tem- poral deceleration and acceleration as the wake passes.

Lou and Hourmouziadis @12# separated this temporal effect from the wake turbulence effect, using downstream control to create an oscillat- ing velocity in their test section.

of mechanical conventional high-lift flap systems, and into the region of Supercirculation (i.e., well beyond BLC).

Because this dramatically changes the airfoil static pressure distribution, the concepts can also be used to modify the aerodynamic moments as desired, as well as increase/decrease the drag and the downstream wake.

Although the noise benefits of Circulation Control have never been shown by anyone through experimentation, it has high potential for reduction of airframe noise and was the subject of this study.

(ref, 38), f n addi ti on to working closely wi th Bsei ng duri ng the devel opmenl, Langl ey researchers have made comprehensive val i dati on and appl i cati on studies, some of which have been reviewed by Luckring, Schoonover, and Frink, in reference 39.

They describe their investigation of convergence techniques for both the wing flow and the near-wake flow as a means of reducing computational cost and present several examples of practical applications.

Based on these and other studies, it appears that the basic version of the theory has provided the most accurate and versatile inviscid approach avai 1 abl e for establ i shi ng the compl ete three-dimensional fl ow fi el d and surface pressure distributions for arbitrary configurations throughout the subsonic flow regime.

iately sized and the system interactions allow for testing key specification points to generate the HPT map.

Working method for this table

Walk the rows in order. Each row must still be true in the PDF that the link opens.

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Wake and separated-flow cases where grid-free methods are discussed in the sources. Verify every figure against the original report before a drawing release.

The library hits for this heading were: Experimental Studies of Low-Pressure Turbine Flows and Flow Control; Application of Circulation Control Technology to Airframe Noise Reduction; Vortex Flow Aerodynamics, volume 1; NASA Hybrid Thermally Efficient Core (HyTEC) Phase 2 Q3’GFY25 to Q2’GFY26 Unlimited Rights Annual Report for CLIN 1 and; CEAS/AIAA/ICASE/NASA Langley International Forum on Aeroelasticity and Structural Dynamics 1999; NACA Report 824 Summary of Airfoil Data.