Hi there, I have an assignment in my Gas Dynamics class where were supposed to compute the flow inside a nozzle given stagnation pressure, temperature and area ratio (throat to exit). I am 80% sure this is given a choked condition. Anyways, we have charts to find the Mach number as a function of area ratio, but the assignment is to create a program in either Excel or MathCad. The only thing I can find is the Area Ratio (area to reference area) as a function of Mach number. Since this equation has two solutions (the sub and supersonic solution) I was wondering if anyone could find out the supersonic solution to the equation (i.e. the top part of the graph). I probably could get an estimate typing in pages and pages of charts, and then drawing a line of best fit, but this hardly seems worthwhile, and accurate. If anyone could give a hand, I'd be very grateful.