Propulsion Nozzle Design: dual_bell
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) |
|---|---|---|---|---|---|---|---|---|---|---|---|
| dual_bell | dualbell_er40_g125 | 0.981 | 0.991 | 0.992 | 3.683 | 40 | 1.25 | Dual bell; inner contour ER=16 for sea level; outer contour ER=40 for altitude; switchover at nozzle lip flow separation; CF_vac = 1.9314*0.992*0.991*0.994 | 0.00702 | 1.748 | 1.907 |
| dual_bell | dualbell_er80_g125 | 0.981 | 0.991 | 0.992 | 4.237 | 80 | 1.25 | Dual bell ER=80 outer; avg CF trajectory gain 3-6% vs fixed-contour bell; J-2X technology demonstration program | 0.00278 | 1.787 | 1.935 |
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