Aerospike Nozzle Altitude Thrust Calculator
Rocket propulsion & hypersonic aerothermodynamics: Compare aerospike plug nozzle continuous altitude compensation, thrust coefficient ($C_f$), and base pressure thrust against traditional bell nozzles.
Chamber & Atmospheric Conditions
Combustion stagnation pressure (~10 MPa)
0 km = Sea Level (1.013 bar), 30 km = Near vacuum
Aerospike Geometry & Gas Properties
Annular throat area
Truncated spike base area
LOX/Methane ~1.22, LOX/LH2 ~1.24
Turbopump exhaust injected at base
How Aerospike Nozzles Self-Compensate
A traditional de Laval bell nozzle has fixed physical walls: at sea level, overexpansion causes flow separation and shock waves; in vacuum, underexpansion wastes potential thrust.
An aerospike has no outer wall: ambient atmospheric air acts as an invisible aerodynamic boundary, compressing the exhaust jet at sea level and allowing it to expand outward at high altitude.
Thrust & Performance Comparison
Aerospike Thrust (F_aero)
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Fixed Bell Nozzle Thrust
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Thrust Coefficients & Advantage
Aerospike C_f
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Altitude self-compensating
Bell Nozzle C_f
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Optimized for single altitude
Base Pressure & Expansion State
Ambient Atmospheric Pressure:
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Aerospike Thrust Advantage:
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Base Recirculation Pressure:
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