Ratio of Exit to Throat Area Post author:maridurai Post published:June 20, 2021 Post category:Aerospace Calculator / Engineering Calculator / Propulsion Calculator The area ratio for a nozzle with the isentropic flow can be expressed in terms of Mach numbers for any points x and y within the nozzle Tags: Exit to Throat Area ratio, propulsion calcualtor, Ratio of Exit to Throat Area Read more articles Next PostConvective Heat Transfer rate per unit area You Might Also Like Helmbold’s Equation June 28, 2021 Specific Impulse June 15, 2021 Balanced Field Length (BFL) Calculator March 17, 2021