Propulsion Nozzle Design: bell_80pct
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) | notes | pressure ratio pe pc (dimensionless) | thrust coeff cf opt (dimensionless) | thrust coeff cf vac (dimensionless) |
|---|---|---|---|---|---|---|---|---|---|---|---|
| bell_80pct | bell80_er100_g120 | 0.983 | 0.992 | 0.994 | 4.147 | 100 | 1.2 | 80% bell; high-ER upper stage; CF_vac = 2.0334*0.994*0.992 | 0.00247 | 1.557 | 2.03 |
| bell_80pct | bell80_er25_g120 | 0.983 | 0.992 | 0.994 | 3.186 | 25 | 1.2 | 80% bell; divergence angle ~10 deg at exit; CF_vac = 1.9680*0.994*0.992 | 0.01494 | 1.477 | 1.959 |
| bell_80pct | bell80_er25_g130 | 0.983 | 0.992 | 0.994 | 3.445 | 25 | 1.3 | 80% bell; gamma=1.30; CF_vac = 1.8694*0.994*0.992 | 0.0119 | 1.374 | 1.862 |
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