MHD Flow-Control for Hypersonic Flight

• Authors: J. Petit , J. Geffray
• Languages of publication: EN

Abstracts

EN

At the beginning of the seventies, experimental research using short duration supersonic shock driven wind tunnel were conducted and showed the efficiency of Lorentz force action on supersonic (Mach 1.4) dense (1 bar) low magnetic Reynolds number hot (10 000 K) argon flows. When working as a generator, the linear Faraday MHD converter was efficient enough, due to high electrical conductivity (3000 S/m) to create a front shock wave at the intake of the constant cross-section MHD converter. Accelerations up to 5000 m/s were obtained in 10 cm long channels. This suggested the possibility to achieve complete shock wave and turbulent wake cancellation, through MHD bypass concept. Such work gave publications in peer-reviewed journals and presentation in international MHD meetings (French Academy of Sciences 1970, Moscow 1983, Tsukuba 1986, Beijing 1992). The work was conducted both through computational simulations (based on the method of characteristics) and hydraulic simulation experiments. We present the synthesis of such studies through a project of a hypersonic vehicle based on an MHD bypass concept, landing under its own steam, using classical turbojets. Then, at Mach 3 and high altitude, MHD controlled inlets are opened. A wall converter slows down the hypersonic incoming air flow, without excessive heating, feeding a ramjet system. The subsequent electric power provides an additional impulse to the flow in the exhaust section. Cruise Mach number: 12. Local Hall parameter regime produces high voltage that, sent to the leading edges, creates a plasma cushion which prevents too high thermal flux. Lift is provided by wave riding technique. Additional rocket propeller could transform it as a reusable space launcher.

Keywords

EN

02.30.Jr; 47.40.Ki; 47.65.-d; 47.85.lb; 52.30.Cv; 52.75.Fk

Discipline

• 47.65.-d: Magnetohydrodynamics and electrohydrodynamics(see also 47.35.Tv Magnetohydrodynamic waves; 52.30.Cv Magnetohydrodynamics, and 52.65.Kj Magnetohydrodynamics and fluid equation in Physics of plasmas and electric discharges; 83.80.Gv Electro- and magnetorheological fluids in Rheology)
• 47.85.lb: Drag reduction
• 52.30.Cv: Magnetohydrodynamics (including electron magnetohydrodynamics)(see also 47.65.-d Magnetohydrodynamics and electrohydrodynamics in fluid dynamics; for MHD generators, see 52.75.Fk; see also 95.30.Qd Magnetohydrodynamics and plasmas in astrophysics)
• 47.40.Ki: Supersonic and hypersonic flows
• 52.75.Fk: Magnetohydrodynamic generators and thermionic convertors; plasma diodes(see also 84.60.Lw, Ny in direct-energy conversion and storage)
• 02.30.Jr: Partial differential equations

• Publisher: Institute of Physics, Polish Academy of Sciences
• Journal: Acta Physica Polonica A
• Year: 2009
• Volume: 115
• Issue: 6
• Pages: 1149-1151

Dates

published

2009-06

Contributors

author

J. Petit

• LAMBDA Laboratory, France

author

J. Geffray

• LAMBDA Laboratory, France

References

• 1. J.P. Petit, Le Mur du Silence, Berlin, 1983. Also available freely in English, Lithuanian, German, Russian, Polish, Spanish, Croatian, Serbian, Romanian at: http://www.savoir-sans-frontieres.com
• 2. B. Lebrun, Ph. D. Thesis, Aix Marseille University, 1987. See: mhdprospects.com
• 3. J.P. Petit, B. Lebrun, in: Proc. 9th Int. Conf. on MHD Electrical Power Generation, Tsukuba, Japan (Nov. 1986), Proc. III, Part 14.E - MHD Flow, art. 5, p. 1359
• 4. Project Ayax, St. Petersburg Gazette 121 (July 6, 2006)
• 5. Patent RU 1803595, A scramjet and its mode of operation (Jan. 8, 1996)
• 6. Patent RU 2138668, Air-breathing magnetogasdynamic engine (Feb. 24, 1998)
• 7. E.P. Gurijanov, P.T. Harsha, in: Proc. 7th Int. Space Planes and Hypersonic Systems and Technologies Conf., Norfolk, VA (Nov. 1996)
• 8. V.L. Fraishtadt, A.L. Kuranov, E.G. Sheikin, JTF, B 68, 43 (1998)

Identifiers

DOI

10.12693/APhysPolA.115.1149