[American Institute of Aeronautics and Astronautics 37th AIAA Plasmadynamics and Lasers Conference -...
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EFFECTS OF MHD INTERACTION IN RENTRY FLIGHT V.A.Bityurin, A.N.Bocharov Institute of High Temperatures of Russian Academy of Sciences, Moscow, Russia [email protected] Experimental and theoretical studies of the MHD flow interaction around aerobodies in a hypersonic ionized air stream are discussed in our earlier papers (see for full list of references [1]) with comments on potential application for flow and flight control for advanced aerospace vehicles. One of the most promising ideas was proposed at the last reentry Symposium at Arcachon [2]. The current work is a continuation of past efforts by the authors’ directed at characterization of MHD flow field interaction over/around a basic geometric configuration with mutually orthogonal magnetic field and velocity vectors. Experimental results from tests conducted with simple models in a hypervelocity MHD accelerator driven wind tunnel facility with ionized air flow at an MHD interaction parameter, S u , of 0.1.are presented and discussed. Distinctive MHD influence on the flow structure around the model was confirmed in experiments. Experimental and numerical simulations with a plate model under angle-of-attack that is representative of an on-board MHD flight system are reported. Improved reentry trajectory calculations including MHD-[2] parachute effects are presented. References 1. V. A. Вityuriп, A.N. Bocharov, et al. Study of MHD Flow Control and On-Board Electrical Power Generation, 44th AIAA Aerospace Sciences Meeting and Exhibit, AIAA Paper 2006- 1008, Reno, Nevada, Jan 9-12, 2006. 2. V. A. Вityuriп, A.N. Bocharov, J.Lineberry, Study of MHD interaction in Re-Entry Flow, In: 4th International Symposium Atmospheric Reentry Vehicles & Systems,21-23 March 2005, Arcachon-France 37th AIAA Plasmadynamics and Lasers Conference 5 - 8 June 2006, San Francisco, California AIAA 2006-3235 Copyright © 2006 by V.A.Bityurin. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
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EFFECTS OF MHD INTERACTION IN RENTRY FLIGHT V.A.Bityurin, A.N.Bocharov
Institute of High Temperatures of Russian Academy of Sciences, Moscow, Russia
[email protected] Experimental and theoretical studies of the MHD flow interaction around aerobodies in a hypersonic ionized air stream are discussed in our earlier papers (see for full list of references [1]) with comments on potential application for flow and flight control for advanced aerospace vehicles. One of the most promising ideas was proposed at the last reentry Symposium at Arcachon [2]. The current work is a continuation of past efforts by the authors’ directed at characterization of MHD flow field interaction over/around a basic geometric configuration with mutually orthogonal magnetic field and velocity vectors. Experimental results from tests conducted with simple models in a hypervelocity MHD accelerator driven wind tunnel facility with ionized air flow at an MHD interaction parameter, Su, of 0.1.are presented and discussed. Distinctive MHD influence on the flow structure around the model was confirmed in experiments. Experimental and numerical simulations with a plate model under angle-of-attack that is representative of an on-board MHD flight system are reported. Improved reentry trajectory calculations including MHD-[2] parachute effects are presented. References 1. V. A. Вityuriп, A.N. Bocharov, et al. Study of MHD Flow Control and On-Board Electrical Power Generation, 44th AIAA Aerospace Sciences Meeting and Exhibit, AIAA Paper 2006-1008, Reno, Nevada, Jan 9-12, 2006. 2. V. A. Вityuriп, A.N. Bocharov, J.Lineberry, Study of MHD interaction in Re-Entry Flow, In: 4th International Symposium Atmospheric Reentry Vehicles & Systems,21-23 March 2005, Arcachon-France
37th AIAA Plasmadynamics and Lasers Conference5 - 8 June 2006, San Francisco, California
AIAA 2006-3235
Copyright © 2006 by V.A.Bityurin. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
