In this paper some experimental results on the effect of the MHD interaction in the shock layer above a test body immersed into a hypersonic argon flow. The hypersonic flow is obtained from the high-enthalpy arc-heated wind tunnel of Alta-CPR (Pisa) at Mach 6. Test at heating chamber stagnation pressures of 0.65, 0.85, and 1 bar. Different magnetic flux density has been applied, in the range of some fraction of tesla. In order to maximize the effect of the MHD interaction the Faraday field is shorted ad a magnetic field perpendicular to the test body surface is used. The emission spectra has been measured by means of an optical multichannel analyzer and a monocromator.
An Experimental Study on the Shock Layer-MHD Interaction in an Hypersonic Flow / L. Biagioni; C.A. Borghi; M.R. Carraro; A. Cristofolini; A. Fantoni; A. Passaro. - STAMPA. - 2:(2005), pp. 434-443. (Intervento presentato al convegno 15th International Conference on MHD Energy Conversion tenutosi a Moscow, Russia nel May 24-27, 2005).
An Experimental Study on the Shock Layer-MHD Interaction in an Hypersonic Flow
BORGHI, CARLO ANGELO;CARRARO, MARIO ROBERTO;CRISTOFOLINI, ANDREA;
2005
Abstract
In this paper some experimental results on the effect of the MHD interaction in the shock layer above a test body immersed into a hypersonic argon flow. The hypersonic flow is obtained from the high-enthalpy arc-heated wind tunnel of Alta-CPR (Pisa) at Mach 6. Test at heating chamber stagnation pressures of 0.65, 0.85, and 1 bar. Different magnetic flux density has been applied, in the range of some fraction of tesla. In order to maximize the effect of the MHD interaction the Faraday field is shorted ad a magnetic field perpendicular to the test body surface is used. The emission spectra has been measured by means of an optical multichannel analyzer and a monocromator.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
