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Propulsion Nozzle Design: conical

conical er60 g125 to conical er8 g130

De Laval (converging-diverging) rocket nozzle design parameters — expansion ratio (Ae/At), exit Mach number, pressure ratio (pe/pc), vacuum and optimum thrust coefficient (CF), discharge coefficient (Cd), divergence efficiency (lambda), and Isp correction factor by nozzle type (conical 15-deg, bell 80%, bell optimum/Rao, plug/aerospike, dual-bell) and gamma (1.20/1.25/1.30). Isentropic relations per Sutton & Biblarz RPE 9th Ed; nozzle efficiency corrections per NASA SP-8120.

Aerospace Engineeringnozzle type: conical5 rowsPage 2 of 2
nozzle typerecord idIsp correction factor (dimensionless)discharge coeff cd (dimensionless)divergence efficiency lambda (dimensionless)exit mach (dimensionless)expansion ratio (dimensionless)gamma ref (dimensionless)half angle deg (deg)pressure ratio pe pc (dimensionless)thrust coeff cf opt (dimensionless)thrust coeff cf vac (dimensionless)
conicalconical er60 g1250.9750.990.9834.006601.25150.004081.4341.908
conicalconical er60 g1300.9750.990.9834.232601.3150.00351.3681.855
conicalconical er8 g1200.9750.990.9832.34381.2150.072411.3911.885
conicalconical er8 g1250.9750.990.9832.38781.25150.068011.3591.854
conicalconical er8 g1300.9750.990.9832.4381.3150.064011.3371.826

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