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- W2326141302 abstract "The effect of plasma generator propulsive efficiency on aircraft fuel requirement is calculated by analysis of a turbojet engine cycle in which the plasma generator electrical power is extracted from the turbine. Using this, it is shown that a previous experimental result appears to indicate substantial and efficient drag reduction with corona from the nose of a low drag body. Electroaerodynamics is revisited, past work is reviewed and a new analytical model for electron distribution near a shock wave in weakly ionised gas is formulated based on plasma sheath theory. The direct action by coulomb force is essentially eliminated as a possible mechanism for the reported plasma effects on shock propagation and aerodynamic drag. Experiments on a sharp-cone/cylinder at Mach 5 in which a discharge is struck between electrodes on the conical ~QCP care thpn Aecm4hm-l -1 IV ..I_ UI”AI UVIVIAVIU. To alter discharge characteristics the nosetip anode was modified to carry a thin needle and then later to exhaust a jet of argon. The effect of the jet without electric discharge is investigated and compared to published results. The results for all configurations tested indicate that the electric discharge and/or argon jet produced small drag reductions at low propulsive efficiency." @default.
- W2326141302 created "2016-06-24" @default.
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- W2326141302 date "1999-01-11" @default.
- W2326141302 modified "2023-09-26" @default.
- W2326141302 title "Electroaerodynamics and the effect of an electric discharge on cone/cylinder drag at Mach 5" @default.
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- W2326141302 doi "https://doi.org/10.2514/6.1999-602" @default.
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