Propulsion Nozzle Design: plug_aerospike
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) |
|---|---|---|---|---|---|---|---|---|---|---|---|
| plug_aerospike | plug_er16_g125 | 0.987 | 0.988 | 0.998 | 2.96 | 16 | 1.25 | Aerospike ER=16; sea level CF approaches vacuum CF due to altitude compensation; X-33 linear aerospike reference point | 0.02479 | 1.726 | 1.87 |
| plug_aerospike | plug_er4_g125 | 0.987 | 0.988 | 0.998 | 1.699 | 4 | 1.25 | Linear/annular aerospike; self-altitude-compensating; CF_vac=1.9288*0.998*0.988*0.975 (kinetic+BL losses included); Pc=1000 psia typical; truncated spike ~25% full length | 0.21432 | 1.335 | 1.874 |
| plug_aerospike | plug_er80_g125 | 0.987 | 0.988 | 0.998 | 4.237 | 80 | 1.25 | Aerospike ER=80; altitude compensation active across ascent trajectory; trajectory-averaged CF_opt 3-7% above fixed-contour bell | 0.00278 | 1.779 | 1.925 |
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