Propulsion Nozzle Design: conical
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.
| nozzle type | record id | Isp correction factor (dimensionless) | discharge coeff cd (dimensionless) | divergence efficiency lambda (dimensionless) | exit mach (dimensionless) | expansion ratio (dimensionless) | gamma ref (dimensionless) | half angle deg (deg) | notes | pressure ratio pe pc (dimensionless) | thrust coeff cf opt (dimensionless) | thrust coeff cf vac (dimensionless) |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| conical | conical_er100_g120 | 0.975 | 0.99 | 0.983 | 4.147 | 100 | 1.2 | 15 | 15-deg half-angle; isentropic gamma=1.20; ER=100 high-vacuum upper stage | 0.00247 | 1.532 | 2.001 |
| conical | conical_er100_g125 | 0.975 | 0.99 | 0.983 | 4.419 | 100 | 1.25 | 15 | 15-deg half-angle; isentropic gamma=1.25 | 0.00207 | 1.453 | 1.927 |
| conical | conical_er100_g130 | 0.975 | 0.99 | 0.983 | 4.713 | 100 | 1.3 | 15 | 15-deg half-angle; isentropic gamma=1.30 | 0.00174 | 1.377 | 1.864 |
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