A r a a t i o n cooled MPD t h r u s t e r was t e s t e d with t h e magnetic f i e l d supplied by a permanent magnet. a t t h e cathode t i p . A t 25 k W arc power t h e maximum magnet temperature w a s 835O K.weight was under 1 kg/kW. The Mm) t h r u s t e r was also t e s t e d with a superconducting magnet t o i n v e s t igate operation a t varying magnetic f i e l d strengths up t o 1 t e s l a . Some increase i n power a a p a b i l i t y was obtained with increasing f i e l d . t h r u s t e r w a s operated with argon propellant and a hollow cathode, arc efficiency was found t o i ncrease with applied magnetic f i e l d strength.
An analysis is presented for calculating the flowfield in supersonic mixed-compression aircraft inlets operating at angle of attack. The flowfield is computed by a steady three-dimensional bicharacteristic method. The bow shock wave and the reflected internal shock wave system are computed by a three-dimensional, discrete shock wave fitting procedure. Viscous and thermal diffusion may be included as source terms in the bicharacteristic method. A production type of computer program capable of determining the flowfield in a variety of axisymmetric mixed-compression supersonic inlets is available. The results of the present analysis agree well with those produced by the two-dimensional method of characteristics when axisymmetric flowfields are computed. For three-dimensional flowfields, the results of the present analysis agree well with experimental data except in regions of high viscous interaction and boundary-layer removal. The present analysis does not compute the boundary layer, nor does it account for boundary-layer bleed.
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