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 Boundary Layer Thickness Calculator by Mohit Kudal March 16, 2021 Nozzle loss coefficient of jet engine calculator March 12, 2021 Speed of sound by using coefficient of stiffness Calculator March 17, 2021