New Horizons Banner

Nozzel Efficiency

NOZZLE KINETIC TERMINAL
GAS DYNAMICS

NOZZLE EFFICIENCY

Drag/Touch to Rotate Gas expansion Vector
EFFICIENCY RATING
0.0%
PERCENTAGE (%)
FLOW QUALITY ASSESSMENT:
AWAITING COMPUTATION LOOP
Kinetic Energy Conversion0.0%
Thermal/Friction Loss Profile0.0%

NEW HORIZONS MISSION CONTROL • NOZZLE THERMODYNAMICS SYSTEM 2026

Pre-Calculated Nozzle Efficiency

Rocket Engineering • ηn / Velocity Coefficient
Merlin 1D
SpaceX Merlin 1D sea-level nozzle. High efficiency bell nozzle with optimized contour.
ηn 0
Bell Nozzle • Sea Level
Merlin Vacuum
SpaceX Merlin Vacuum (MVac). Large expansion ratio nozzle with excellent vacuum efficiency.
ηn 0
High ε • Vacuum
Raptor Sea Level
SpaceX Raptor sea-level nozzle. Full-flow staged combustion with advanced contour design.
ηn 0
Bell • Methalox
Raptor Vacuum
SpaceX Raptor Vacuum. Extremely high expansion ratio nozzle optimized for vacuum performance.
ηn 0
High ε • Vacuum
F-1 Engine
Rocketdyne F-1 (Saturn V). Large bell nozzle of the 1960s era with good but not modern efficiency.
ηn 0
Bell • LOX/RP-1
SSME / RS-25
Space Shuttle Main Engine. Highly optimized dual-bell capable contour for high efficiency.
ηn 0
High Performance • LOX/LH₂
RD-180
NPO Energomash RD-180. Twin-nozzle design with excellent oxidizer-rich staged combustion efficiency.
ηn 0
Twin Bell • LOX/RP-1
Vulcain 2
Ariane 5 Vulcain 2. European LOX/LH₂ nozzle with regenerative cooling and high efficiency.
ηn 0
Bell • LOX/LH₂
RL10
Aerojet Rocketdyne RL10. Classic high-efficiency expander-cycle vacuum nozzle.
ηn 0
Expander • Vacuum
J-2
Rocketdyne J-2 (Saturn V upper stages). 1960s vacuum-optimized bell nozzle.
ηn 0
Bell • LOX/LH₂
BE-4
Blue Origin BE-4. Modern methalox nozzle designed for high efficiency and reusability.
ηn 0
Bell • Methalox
RS-68
Rocketdyne RS-68 (Delta IV). Large gas-generator LOX/LH₂ nozzle.
ηn 0
Bell • LOX/LH₂
LE-7A
Mitsubishi LE-7A. Japanese staged-combustion nozzle with high contour efficiency.
ηn 0
Staged • LOX/LH₂
LE-5B
Mitsubishi LE-5B. High-expansion vacuum nozzle with excellent efficiency.
ηn 0
Expander-Bleed • Vacuum
RD-107 / RD-108
Russian RD-107/108 (Soyuz). Multi-chamber nozzles with good but older design efficiency.
ηn 0
Multi-Chamber • LOX/RP-1
RD-0120
Russian RD-0120 (Energia). High-performance LOX/LH₂ nozzle.
ηn 0
Staged • LOX/LH₂
HM7B
Ariane 5 HM7B upper-stage nozzle. Compact high-efficiency vacuum design.
ηn 0
Vacuum • LOX/LH₂
BE-3
Blue Origin BE-3 (New Shepard). Efficient LOX/LH₂ nozzle for suborbital flights.
ηn 0
Tap-Off • LOX/LH₂
Rutherford
Rocket Lab Rutherford. Small electric-pump engine nozzle with good efficiency for its size.
ηn 0
Small Bell • LOX/RP-1
Prometheus
ESA Prometheus reusable methalox nozzle. Designed for cost-effective high efficiency.
ηn 0
Reusable • Methalox
RD-191
NPO Energomash RD-191 (Angara). Single-chamber high-efficiency ORSC nozzle.
ηn 0
ORSC • LOX/RP-1
YF-100
Chinese YF-100. Modern oxidizer-rich staged combustion nozzle.
ηn 0
ORSC • LOX/RP-1
YF-77
Chinese YF-77 (Long March 5). Gas-generator LOX/LH₂ nozzle.
ηn 0
Gas Generator • LOX/LH₂
RL10-B-2
RL10-B-2 with extendible nozzle. Extremely high vacuum nozzle efficiency.
ηn 0
Extendible • Vacuum
Solid Rocket Booster
Space Shuttle / SLS SRB nozzle. Solid motors typically have slightly lower nozzle efficiency.
ηn 0
Solid • APCP
GEM-63 / Castor
Typical solid strap-on booster nozzle efficiency (GEM, Castor family).
ηn 0
Solid Strap-on
CE-20
ISRO CE-20 (GSLV Mk III). Modern Indian LOX/LH₂ upper-stage nozzle.
ηn 0
Vacuum • LOX/LH₂
Vikas
ISRO Vikas engine. Hypergolic nozzle with good efficiency for its class.
ηn 0
Hypergolic • Gas Generator
AJ10
Aerojet AJ10 hypergolic engine. Reliable pressure-fed nozzle design.
ηn 0
Pressure-Fed • Hypergolic
RD-0124
Russian RD-0124 (Soyuz upper stage). High-efficiency staged-combustion nozzle.
ηn 0
Staged • LOX/RP-1
VINCI
Ariane 6 Vinci expander-cycle engine. State-of-the-art European vacuum nozzle efficiency.
ηn 0
Expander • Vacuum
BE-3U
Blue Origin BE-3U upper-stage nozzle. Vacuum-optimized version of BE-3.
ηn 0
Vacuum • LOX/LH₂
Kestrel
SpaceX Kestrel (Falcon 1). Simple pressure-fed nozzle with moderate efficiency.
ηn 0
Pressure-Fed • LOX/RP-1
NK-33 / AJ-26
Kuznetsov NK-33. High-performance ORSC nozzle from the N-1 program.
ηn 0
ORSC • LOX/RP-1
RS-68A
Upgraded RS-68A nozzle with improved contour and efficiency over original RS-68.
ηn 0
Improved Bell • LOX/LH₂
Early Conical Nozzle
1950s–60s conical nozzles. Lower efficiency due to divergence losses.
ηn 0
Conical • Historical
Ideal Bell (Theoretical)
Theoretical ideal contoured bell nozzle with minimal divergence and friction losses.
ηn 0
Ideal Contour
Aerospike (Linear)
Linear aerospike nozzle efficiency (altitude-compensating). Good average across altitudes.
ηn 0
Altitude Compensating
Dual-Bell Nozzle
Experimental dual-bell nozzle. High efficiency in both sea-level and vacuum modes.
ηn 0
Dual-Mode • Research
Advanced Vacuum
Modern high-expansion-ratio vacuum nozzles (ε > 100) with near-ideal efficiency.
ηn 0
ε > 100 • Vacuum

Expansion Sync

Nozzle Area Ratio (ε). Optimizing the ratio between the throat area and exit area to maximize the conversion of enthalpy into kinetic energy.

  • 📐 Mach: Exit Velocity Vectoring.
  • 🔍 Enthalpy: Thermal-to-Kinetic Shift.
  • ⚙️ Geometry: Bell vs. Conical Profile.
AREA RATIO (ε)
📐
EXPANSION
150:1
VACUUM OPTIMIZED

Choke Sync

Choked Flow Dynamics. Achieving Mach 1 at the nozzle throat (At) to establish a mass flow rate independent of downstream pressure.

  • ⚡ Sonic: M=1 Velocity Lock.
  • ⚖️ Mass: Propellant Throughput Peak.
  • 🛡️ Thermal: High Flux Heat Loading.
CRITICAL POINT
⚡
VELOCITY
MACH 1.0
THROAT CHOKE SECURE

Ambient Sync

Under/Over Expansion. Managing the Pe/Pa ratio to avoid shock-induced flow separation or efficiency losses at sea level.

  • 📉 Shock: Mach Diamond Mitigation.
  • 🌪️ Sep: Flow Detachment Control.
  • ⚖️ Balance: Pe = Pa (Ideal Thrust).
PRESSURE RATIO
📉
AMBIENT
SEA LEVEL
OVER-EXPANDED STATE

Kinetic Sync

Characteristic Velocity (c*). Quantifying combustion efficiency and the nozzle's ability to convert gas pressure into exit velocity (Ve).

  • 🚀 ISP: Specific Impulse Mapping.
  • 💨 Ejecta: High-Hypersonic Exhaust.
  • 🔥 Plume: Divergence Angle Loss.
SPECIFIC IMPULSE
🚀
EXIT VEL
4.5 km/s
KINETIC PEAK SYNC

Boundary Sync

Boundary Layer Mapping. Analyzing the viscous drag and heat transfer along the nozzle wall that reduces total nozzle efficiency (η).

  • 🧼 Viscosity: Shear Stress Loss.
  • 🌡️ Ablation: Wall Material Decay.
  • 📉 Drag: Momentum Deficit Sync.
VISCOUS LOSS
🧼
DRAG COEFF
0.04
WALL FLOW NOMINAL

Isentropic Sync

Efficiency Index (ηn). Comparing the real-world adiabatic expansion to the theoretical isentropic ideal.

  • 📊 Ratio: Real vs. Ideal Work.
  • 🌀 Entropy: Irreversibility Tracking.
  • 🏁 Output: Final Thrust Vector.
EFFICIENCY INDEX
📊
η INDEX
0.98
FLOW EFFICIENCY PEAK

Recommended Tools

View All

Loading recommended tools...

Explore More!

rocket_launch
Voyager
Rocket Engineering AI
Hi! I’m Voyager.
Your Rocket Engineering AI assistant.
Ask me about Max-Q, delta-v, TWR, specific impulse, staging, re-entry, nozzle design, or any formula on this site.
I explain everything step-by-step with clear lists.