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Numerical simulation of turbulent compressible flows in a C-D nozzle with different divergence angles | ||
| Journal of Heat and Mass Transfer Research | ||
| مقاله 5، دوره 1، شماره 2، بهمن 2014، صفحه 93-100 اصل مقاله (681.69 K) | ||
| نوع مقاله: Full Length Research Article | ||
| شناسه دیجیتال (DOI): 10.22075/jhmtr.2014.184 | ||
| نویسندگان | ||
| Mohammad Hadi Hamedi Estakhrsar1؛ Mehdi Jahromi* 2 | ||
| 1Malek-Ashtar University of Technology, Tehran, Iran. | ||
| 2Malek-Ashtar University of Technology, Tehran, Iran | ||
| تاریخ دریافت: 21 آذر 1392، تاریخ بازنگری: 04 اسفند 1392، تاریخ پذیرش: 19 خرداد 1393 | ||
| چکیده | ||
| Compressible gas flow inside a convergent-divergent nozzle and its exhaust plume at different nozzle pressure ratios (NPR) have been numerically studied with several turbulence models. The numerical results reveal that, the SST k–ω model give the best results compared with other models in time and accuracy. The effect of changes in value of divergence half-angle (ε ) on the nozzle performance, thrust coefficient ( Cf ) and discharge coefficient ( C d) has been investigated numerically. The predicted results show that for a given divergence angle, the thrust coefficient (Cf ) increases by increasing nozzle pressure ratio. Also, for a given nozzle pressure ratio, the thrust coefficient increases as the nozzle divergence angle decreases. When the CD nozzle is chocking, the value of discharge coefficient is independent of nozzle pressure ratio and also for a given nozzle pressure ratio, the discharge coefficient increases as the divergence nozzle angle (ε) increases. | ||
| کلیدواژه‌ها | ||
| Numerical simulation؛ converging-diverging nozzle؛ Divergence angle؛ Thrust coefficient؛ Discharge Coefficient؛ Static temperature | ||
| مراجع | ||
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[1]. K. K. Quintao, Design Optimization of Nozzle Shapes for Maximum Uniformity of Exit Flow,Florida International University,M.S. Thesis, (2012).
[2]. A. M. Geatz, A Prediction Code for the Thrust Performance of Two Dimensional, Non-Axisymmetric, Converging Diverging Nozzles,Air Force Institute of Technology,PH.D Thesis, (2005).
[3]. Q. Xiao, H.M. Tsai , D. Papamoschou, Numerical Study of Jet Plume Instability from an Over-expanded Nozzle, 45th AIAA Aerospace Sciences Meeting and Exhibit, Nevada, AIAA, (2007).
[4]. A.Hamed,C.Vogiatzist, Over-expanded Two-Dimensional Convergent-Divergent Nozzle Performance, Effects of Three-Dimensional Flow Interactions, Journal ofPropulsion and Power,14, 234-240, (1998).
[5]. A.Hamed, C.Vogiatzist, Three-Dimensional Flow Computations and Thrust Predictions in 2DCD Over-expanded Nozzles, AIAA paper 97-0030, (1997).
[6]. A. Balabel, A.M. Hegab, S. Wilson, M. Nasr, S. El-Behery, Numerical Simulation of Turbulent Gas Flow in a Solid Rocket Motor Nozzle, 13th International Conference on Aerospace Science and Aviation Technology, Egypt, (2009).
[7]. N. J. Georgiadis, D. Papamoschou, Computational Investigation of High-Speed Dual Stream Jets, AIAA 2003-3311, (2003).
[8]. C. F.Chenault, P.Beran, Numerical Investigation of Supersonic Injection Using a Reynolds-Stress Turbulence Model, AIAA Journal, 37, 1257-1269, (1999).
[9]. H.Zhang, R.So, T.Gatski, C. Speziale, a Near-Wall Second-Order Closure for Compressible Turbulent Flows, Near-Wall Turbulent Flows, edited by R. So, C. Speziale, and B. Launder, Elsevier, New York, 209-218,(1993).
[10]. M.A. Dembowski, N.J. Georgiadis, an Evaluation of Parameters Influencing Jet Mixing Using the WIND Navier-Stokes Codes, NASA/TM-211727,(2002).
[11]. K. A. Park, Y. M. Choi, H. M. Choi, T. S. Cha, B.H. Yoon,The Evaluation of Critical Pressure Ratios of Sonic Nozzles at Low Reynolds Numbers. Flow Measure, Instrum,12, 37–41, (2001).
[12]. J. S. Paik, K. A. Park, J. T. Park, Inter-Laboratory Comparison of Sonic Nozzles atKRISS,Flow Measure, Instrum, 11, 339–344, (2000).
[13]. R. A. Ahmad, Discharge Coefficients and Heat Transfer for Axisymmetric Supersonic Nozzles. Heat Transfer Eng, 22, 40–61, (2001).
[14]. H. D. Kim, J. H. Kim, K. A. Park, T.Setoguchi, S. Matsuo, Computational Study of the Gas Flow Through a Critical Nozzle. Proc. Instn. Mech. Engrs, 217, 1179–1189, (2003).
[15]. A. Balabel, A.M. Hegab, M. Nasr, Samy M. El-Behery, Assessment of Turbulence Modeling for Gas Flow in Two-Dimensional Convergent–Divergent Rocket Nozzle, Applied Mathematical Modelling, 35, 3408–3422, (2011).
[16]. V.S,Krishnamurty, W.Shyy, Effect of Wall Roughness on the Flow through Converging-Diverging Nozzles, Journal of Propulsion and Power, 13, 753-762, (1997).
[17]. M.L. Mason, L.E. Putnam,J.R. Richard, The Effect of Throat Contouring on Two Dimensional Converging-Diverging Nozzles at Static Condition, NASA Technical Paper 1704, (1980).
[18]. Fluent, User’s Guide Fluent 6.3.26, Fluent Incorporated, Lebanon, NH, (2006).
[19]. B. E. Launder, G. J. Reece, and W. Rodi, Progress in the Development of aReynolds-Stress Turbulence Closure, J. Fluid Mech., 68, 537-566, (1975).
[20]. B. E. Launder, D. B. Spalding, Mathematical Models of Turbulence, AcademicLondon, 169-189, (1972).
[21]. F. R.Menter, Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications, AIAA journal, 32, 1598-1605, (1994). | ||
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