A graphical method for obtaining the two-dimensional supersonic flow with moderate heat addition is presented. The basic equations were derived for flows in which the total temperature has a-continuous variation with displacement in the direction of the flow. For flows at constant total temperatures before heat addition and with total temperature varying only in the direction of the streamlines, simpli fied forms of the basic equations were obtained from which working charts were plotted to facilitate, construction of the flow. The working charts cover the range of Mach number from 1.3 to 5.0. The application of the method and the charts are illustrated by a simple example/ giving the flow around a curved surface with addition of heat in an adjacent finite layer where the initial total temperature of the flow is the same on all streamlines and lines of constant total temperature in the heated portion of the flow lie approximately normal to the streamlines.
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