Fuselage Surface Pressure Effects due to Wing Interferences
Keywords:
RANS, Compressible, Onera M6, Interference, Design.Abstract
A streamlined fuselage with a rounded cross-sectional area attached with Onera M6 wing was tested using a compressible RANS CFD. Coupled with k-omega SST turbulent model, the craft was tested at 0.8359 Mach which corresponds to 11.72 x 106 Reynolds number. At 3.06? wing incidence angle, this simulation is to highlight the fuselage surface pressure variations at the interference region for preliminary aircraft design consideration. By keeping up closely with the physically tested wing through wind tunnel, the results of this simulation can be justified.
References
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[2] Shankar, V., & Malmuth, N. (1981). Computational and Simplified Analytical Treatment of Transonic Wing/Fuselage/Pylon/Store Interactions. Journal of Aircraft, 18(8), 631-637.
[3] Caughey, D. A., & Jameson, A. (1979). Numerical calculation of transonic potential flow about wing-body combinations. AIAA Journal, 17(2), 175-181.
[4] Boppe, C. W. (1980). Transonic flow field analysis for wing-fuselage configurations.
[5] Ross, J., CORSIGLIA, V., & VOGEL, J. (1981, August). Full-scale wind-tunnel study of wing-fuselage interaction and comparison with paneling method. In Aircraft Systems and Technology Conference (p. 1666).
[6] Chigier, N. A., & Corsiglia, V. R. (1972). Wind-tunnel studies of wing wake turbulence. Journal of Aircraft, 9(12), 820-825.
[7] Liebhardt, B., & Lütjens, K. (2011). An Analysis of the Market Environment for Supersonic Business Jets. German Aerospace Center (DLR)–Air Transportation Systems, Hamburg.
[8] https://www.boeing.com/resources/boeingdotcom/company/about_bca/startup/pdf/historical/747-400-passenger.pdf
[9] https://www.airbus.com/content/dam/corporate-topics/publications/backgrounders/Backgrounder-Airbus-Commercial-Aircraft-A380-Facts-and-Figures-EN.pdf
[10] Menter, F. R. (1994). Two-equation eddy-viscosity turbulence models for engineering applications. AIAA journal, 32(8), 1598-1605.
[11] Rahman, U. A., & Mustapha, F. (2015, February). Validations of OpenFoam Steady State Compressible Solver Rhosimplefoam. In International Conference on Mechanical and Industrial Engineering.
[12] Patankar, S. V. (1980). Numerical Heat Transfer and Fluid Flow Taylor & Francis. New York.
[13] Fergizer, J. H., & Peric, M. Computational Methods for Fluid Dynamics. 2002.
[14] Schmitt, V. and F. Charpin, "Pressure Distributions on the ONERA-M6-Wing at Transonic Mach Numbers," Experimental Data Base for Computer Program Assessment. Report of the Fluid Dynamics Panel Working Group 04, AGARD AR 138, May 1979.
[15] http://www.cfd-online.com/Wiki/Turbulence_free-stream_boundary_conditions - 18/07/2013.
[16] Jasak, H. (1996). Error analysis and estimation for the finite volume method with applications to fluid flows.
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Published
2018-09-17
How to Cite
Abdul Rahman, U., & Mustapha, F. (2018). Fuselage Surface Pressure Effects due to Wing Interferences. American Scientific Research Journal for Engineering, Technology, and Sciences, 46(1), 218–228. Retrieved from https://asrjetsjournal.org/index.php/American_Scientific_Journal/article/view/4390
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