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Numerical simulation of roll induced moment of cruciform tactical missiles
Institution:1. LML, Cité scientifique, 59655 Villeneuve d''Ascq cedex, France;2. ONERA, 29 avenue Division Leclerc, 92322 Châtillon cedex, France;3. Département E/ECN, Aerospatiale, `Missiles'' Division, Centre des Gâtines, 91370 Verrieres-Le-Buisson, France;1. Beijing Electro-mechanical Engineering Institute, Beijing, 100074, People''s Republic of China;2. School of Aerospace Engineering, Beijing Institute of Technology, Beijing, 100081, People''s Republic of China;3. Beijing Institute of Automatic Control Equipment, Beijing, 100074, People''s Republic of China;1. School of Engineering, Deakin University, Waurn Ponds, VIC 3216, Australia;2. School of Software and Electrical Engineering, Swinburne University of Technology, Hawthorn, VIC 3122, Australia;1. Université Libre de Bruxelles, BEAMS department, 50, F.D. Roosevelt av., 1050 Brussels, Belgium;2. Université de Lyon, CNRS INSA-Lyon, LaMCoS UMR5259, F-69621 Villeurbanne, France;1. Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai, China, 200072;2. Shanghai Key Laboratory of Mechanics in Energy Engineering, Shanghai, China, 200072;1. Department of Rheumatology/Immunology, Shanghai Children’s Medical Center, Shanghai Jiao Tong University School of Medicine, Shanghai 200127, China;2. Division of Immunology, Institute of Pediatric Translational Medicine, Shanghai Children’s Medical Center, Shanghai Jiao Tong University School of Medicine, Shanghai 200127, China;3. Division of Allergy and Immunology, Department of Pediatrics, Virginia Commonwealth University, Richmond, VA, 23298, USA
Abstract:This paper presents a numerical evaluation of the induced roll moment of cruciform missiles by a turbulent Navier–Stokes solver. The numerical results have been computed with a high resolution implicit upwind scheme. Comparisons with experiments performed at ONERA show a good agreement as well as a decisive improvement over numerical simulations based on Euler equations. Results are presented for subsonic and supersonic onflow conditions and two different configurations: fuselage-fins and fuselage-wing-fins. Comparative detailed analysis results in the origin of the rolling moment as well as the contributions of the different lifting surfaces.
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