Computational Study of Interaction of Turbulent Offset Jet and Wall Jet Flow Using Low-Reynolds Number Model

Author(s):  
Sushil Kumar Rathore ◽  
Sanjay Singh Rathore ◽  
Sumanta Chaudhuri
Author(s):  
Vishwa Mohan Behera ◽  
Sushil Rathore

Abstract The present study reports the numerical simulation of turbulent plane offset jet flow over a moving plate. The effect of plate velocity on various flow characteristics are discussed in detail including the special case of a stationary plate. For turbulence closure, low-Reynolds number (LRN) model proposed by Yang and Shih (YS) is applied because it is computationally robust and reported to perform well in many complex flow situations. The computations have been carried out with a Reynolds number of 15000 for various offset ratios (OR=3, 7 and 11) for plate to jet velocity ratios in the range 0-2. Finite volume method with a staggered grid arrangement has been used to solve the transport equations. The application of LRN model along with integration to wall approach enables to capture one closed loop of Moffatt vortex near the left corner of the wall for the stationary plate case. The spreading of jet has been found to reduce with increase in the plate velocity. The jet half-width lies very close to the wall for the plate to jet velocity 1.5 and 2. For two extreme limits of plate velocity i.e. Uplate = 0 and 2, the nearly self-similar profiles are observed at different axial locations in the wall jet region. Also, the flow is observed to exhibit nearly self-similar behavior when velocity profiles are plotted for various offset ratios at a given axial location in the wall jet region for Uplate = 0 and 2.


2000 ◽  
Author(s):  
Ajit Pal Singh ◽  
S. H. Winoto ◽  
D. A. Shah ◽  
K. G. Lim ◽  
Robert E. K. Goh

Abstract Performance characteristics of some low Reynolds number airfoils for the use in micro air vehicles (MAVs) are computationally studied using XFOIL at a Reynolds number of 80,000. XFOIL, which is based on linear-vorticity stream function panel method coupled with a viscous integral formulation, is used for the analysis. In the first part of the study, results obtained from the XFOIL have been compared with available experimental data at low Reynolds numbers. XFOIL is then used to study relative aerodynamic performance of nine different airfoils. The computational analysis has shown that the S1223 airfoil has a relatively better performance than other airfoils considered for the analysis.


2007 ◽  
Vol 52 (10) ◽  
pp. 935-957 ◽  
Author(s):  
Jamel Kechiche ◽  
Hatem Mhiri ◽  
Georges Le Palec ◽  
Philippe Bournot

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