Improvement perspectives of aerodynamic and thrust-energetic parameters of hypersonic aircraft and engines when using algorithmic discharges and plasmoid formations

• Published in: Acta astronautica 1998-07, Vol.43 (1), p.31-34
• Main Authors: Burdakov, V.P, Baranovsky, S.I, Klimov, A.I, Lebedev, P.D, Leonov, S.B, Pankova, M.B, Puhov, A.P
• Format: Article
• Language: English
• ISSN: 0094-5765; 1879-2030
• DOI: 10.1016/S0094-5765(97)00207-5

One of the most inviting hypersonic aircraft (HA) research projects involves a draft engine-uniflow air-jet engine, starting turbojet engine (speed rated at Mach 2.5), and a maneuverable fluid engine (in orbit). The authors propose a new method of aerophysical influence on the flow-around airstream of the HA, along with those used in the project: traditional methods of wave-drag reduction, friction and reduction of the heat-exchange process, application of new technological materials, and original methods of local and total cooling. The aerophysical control methods are based on the application of algorithmic high frequency and microwave discharges, and non-thermal nonequilibrium structured plasmoid formations (ball lightning models directed upstream with the reduction of aerodynamic drag, or distributed over the wing surfaces increasing Cy and, in the wake, increasing the wake pressure, causing an additional decrease of Cx). (AIAA)