FLOW COMPUTATION THROUGH THE PASSAGE BOUNDED BY THE DISH AND SUPPORTS OF THE AWACS
Main Article Content
Abstract
A numerical method has been introduced to predict the flow through a complex geometry bounded by the fuselage, airfoil supports and rotating dish of the AWACS. The finite volume computational approach is used to carry out all computations with staggered grid arrangement. The (k-ε) turbulence model is utilized to describe the turbulent flow. The solution algorithm is based on the technique of automatic numerical grid generation of curvilinear coordinate system having coordinate lines coincident with the boundary counters regardless of its shape. A general coordinate transformation is used to represent complex geometries accurately and the grid is generated using a system of elliptic partial differential equations technique. The extension of the SIMPLE algorithm for compressible flow is used to obtain the required solution.. The results obtained in the present work show that the moving boundary (the rotating dish) has small effects on the free stream and the effects vanish after short distance away from the lower surface of the rotating dish along the span distance. The results of the proposed numerical method show good agreement with available results obtained in literatures.
Article Details
Section
How to Cite
References
Al-Abbassy, Y. T., 2003: Prediction of the three dimensional compressible turbulent fluid flow inside a gas turbine impeller. Ph. D. Thesis, Mech. Dept. University of Baghdad.
Al-Deroubi, N. N., 2001: Analysis of two dimensional flow between turbomachinery blade using body fitted coordinate system. M. Sc. Thesis, Mech. Dept. University of Baghdad.
Atta, Z. W., 2000: Quasi-three dimensional low speed viscous flow between axial compressor cascade blades. M. Sc. Thesis, Mech. Dept. University of Baghdad.
Ferziger, J. H. and Peric, M, 1999: Computational Methods for Fluid Dynamics, 2nd edition, Springer, Berlin.
Gogezh, M. M., 2000: Three dimensional turbulent flow between two axial compressor blades using body fitted coordinate system. Ph. D. Thesis, Mech. Dept. University of Baghdad.
Karki, K. C. and Patankar, S. V., 1989: Pressure based calculation procedure for viscous flows all speeds in arbitrary configurations. AIAA, J. vol. 27, 1167-1174.
Launder, B.E., and Spalding, D.B., 1973: Mathematical Models of Turbulence, Academic Press, London.
Molt, A. and Srivatsa, S. K., 1977: KORA-2 A computer code for axi-symetrical combustion chambers. Chan computer code 201, London, England.
Patankar, N. A., Singh, P., Joseph, D. D., Glowinski, R. & Pan, T.-W. 2000: A new formulation of the distributed Lagrange ultiplier/fictitious domain method for particulate flows. Int. J. Multiphase Flow 26, 1509-1524.
Patankar, S. V., 1980: Numerical heat transfer and fluid flow. Hemisphere publishing Corporation, McGraw-Hill Book Co.
Rhie, C. M. and Chow, W. L., 1983: Numerical study of the turbulent flow past an airfoil with trailingedge separation. AIAA J., Vol. 21, no. 11, 1525-1532.
Thompson, J. F., Thames, F. C. and Mastin, C. W., 1974: Automatic numerical generation of body fitted curvilinear coordinate system for field containing any number of arbitrary two dimensional bodies. J. Comp. Phys., vol. 15, 299-319.
Thompson, J. F., Thames, F. C. and Mastin, C. W., 1976: TOMCAT-A code for numerical generation of boundary fitted curvilinear coordinate systems on fields containing any number of arbitrary two dimensional bodies. J. Comp. Phys., vol. 24, 275-302.
Versteeg, H. K. and Malalasekera, W., 1995: An introduction to computational fluid dynamics, the finite volume method. Longman Scientific and technical.
Wang, Y. and Komori, S., (a) 1998: Prediction of duct flows with a pressure base procedure. Numer. Heat Trans., vol. 33, No. 7, 723-748.
Wang, Y. and Komori, S., (a) 1998: Prediction of duct flows with a pressure base procedure. Numer. Heat Trans., vol. 33, No. 7, 723-748.