Figure 6-7 - uploaded by Benjamin Abban
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a: Flow pattern in the lee of the pier 6-6 Figure 6-7b: Flow pattern in the lee of the pier 6-7 Figure 6-8a: Velocity fields predicted by different turbulence models in front of pier 6-8 Figure 6-8b: Velocity fields predicted by different turbulence models in front of pier 6-9 Figure 6-9a: Movability Numbers predicted by k-& model within the vicinity of the pier Figure 6-9b: Movability Numbers predicted by RSM within the vicinity of the pier Figure 6-10: Movability Numbers predicted by RSM with enhanced wall functions for Experiment 1
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Department, TR59030 Tekirdag-TURKEY. fkonukcu@nku.edu.tr http://fkonukcu.cv.nku.edu.tr/ Department, TR59030 Tekirdag-TURKEY. salbut@nku.edu.tr http://salbut.cv.nku.edu.tr/ Tekirdağ
Citations
... Wall treatment approaches[26] Bear in mind that the Low-Reynolds-Number approach does not refer to the Reynolds number Re of equation 2.4, but to the turbulent Reynolds number Re t shown in equation 2.20. This number is low in the viscous sublayer, and this justifies the name given to this approach. ...
This thesis presents the results of computational fluid dynamics (CFD) design calculations of a subsonic nozzle operating at Mach number 0.85 in a transonic linear cascade wind tunnel. The purpose of the nozzle is to accelerate a fluid by decreasing the pressure energy and raising the kinetic one. The challenge in a nozzle design is to obtain uniform flow at the desired velocity. This parameter is examined in this project measuring the total pressure loss, boundary layer thickness, and exit flow angle. These measures have been the drivers for the present nozzle design.
A quasi-one-dimensional approach implemented in Python programming was performed for the first design phase of the project. Subsequently, a mesh independence study was done and five wall contours were tested using the software package from ANSYS (ICEM CFD & CFX). The purpose of the CFD simulations was to determine the nozzle's optimum geometry to achieve flow uniformity in the nozzle outlet. It was found that the 5th order polynomial wall contour proposed by NASA was the best one concerning flow uniformity. Afterwards, the drawings and CAD model of the selected nozzle was produced with Autodesk Inventor.
Finally, a turbulence model comparison among SST and k − is presented. It was confirmed that k − can be used for saving computational resources without loosing significant accuracy in the CFD simulation results.
