Ratio of the diffuser throat area to the nozzle throat area at sonic flow when the temperature is constant in an adiabatic flow Calculator

At,2 (Diffuser Throat Area): This is the cross-sectional area of the throat of the diffuser section of a propulsion system. The diffuser is the component responsible for slowing down and compressing incoming air or propellant flow before it enters the combustion chamber or nozzle. The area of the diffuser throat is an important parameter in optimizing the performance of the propulsion system. At,1 (Nozzle Throat Area): This is the cross-sectional area of the throat of the nozzle of the propulsion system. The nozzle is responsible for accelerating the exhaust gases to generate thrust. The area of the nozzle throat is a critical design parameter that affects the speed and efficiency of the exhaust gas flow. 

• Ratio of the diffuser throat area to the nozzle throat area (At,2/At,1)
• Pressure at the nozzle of sonic flow (p1*) in N/m^2
• Pressure at the diffuser of sonic flow (p2*) in N/m^2