Exhaust Velocity

GAS DYNAMICS CORE

PROPULSION ARCHITECTURE MODEL

SPECIFIC IMPULSE SYSTEM RATING (I_sp - SECONDS)

STANDARD GRAVITY ACCELERATION (g - M/S²)

JET DYNAMICS

EXHAUST VELOCITY

Drag/Touch to Rotate Gas Expansion Grid

EFFECTIVE EXIT VELOCITY (V_e)

0.0

METERS PER SECOND (M/S)

PERFORMANCE BOUNDARY STATUS:

INITIALIZING TELEMETRY ENGINE

Velocity Core Mach Number (Estimated Sea Level Air)Mach 0.00

Kinetic Energy per Unit Mass (KE_mass)0.00 MJ/kg

NEW HORIZONS MISSION CONTROL • AEROTHERMODYNAMICS ANALYSIS LAB 2026

Pre-Calculated Exhaust Velocity

Rocket Engineering • v_e / Effective Exhaust Velocity

Merlin 1D SL

SpaceX Merlin 1D sea-level exhaust velocity. LOX/RP-1 gas-generator cycle.

v_e 0 m/s

Sea Level • LOX/RP-1

Merlin Vacuum

SpaceX Merlin Vacuum (MVac). Optimized high-expansion nozzle for upper stage.

v_e 0 m/s

Vacuum • LOX/RP-1

Raptor Sea Level

SpaceX Raptor sea-level methalox engine. Full-flow staged combustion.

v_e 0 m/s

Sea Level • CH₄/LOX

Raptor Vacuum

SpaceX Raptor Vacuum. High-performance vacuum-optimized methalox engine.

v_e 0 m/s

Vacuum • CH₄/LOX

F-1 Engine

Rocketdyne F-1 (Saturn V). Most powerful single-chamber engine ever flown.

v_e 0 m/s

Sea Level • LOX/RP-1

SSME / RS-25

Space Shuttle Main Engine vacuum exhaust velocity. Highest operational chemical Isp.

v_e 0 m/s

Vacuum • LOX/LH₂

RD-180

NPO Energomash RD-180. High-pressure oxidizer-rich staged combustion.

v_e 0 m/s

Sea Level • LOX/RP-1

Vulcain 2

Ariane 5 Vulcain 2 vacuum exhaust velocity. European LOX/LH₂ first-stage engine.

v_e 0 m/s

Vacuum • LOX/LH₂

RL10 Vacuum

Aerojet Rocketdyne RL10. Classic high-performance expander-cycle upper stage.

v_e 0 m/s

Vacuum • LOX/LH₂

J-2

Rocketdyne J-2 (Saturn V upper stages). LOX/LH₂ vacuum exhaust velocity.

v_e 0 m/s

Vacuum • LOX/LH₂

BE-4

Blue Origin BE-4 methalox engine. Used on New Glenn and Vulcan Centaur.

v_e 0 m/s

Sea Level • CH₄/LOX

RS-68

Rocketdyne RS-68 sea-level exhaust velocity (Delta IV).

v_e 0 m/s

Sea Level • LOX/LH₂

RS-68 Vacuum

RS-68A vacuum-optimized performance with higher expansion ratio.

v_e 0 m/s

Vacuum • LOX/LH₂

LE-7A

Mitsubishi LE-7A sea-level exhaust velocity (H-IIA/H-IIB).

v_e 0 m/s

Sea Level • LOX/LH₂

LE-5B

Mitsubishi LE-5B vacuum exhaust velocity. High-performance Japanese upper stage.

v_e 0 m/s

Vacuum • LOX/LH₂

RD-107

Russian RD-107 (Soyuz boosters). Classic LOX/RP-1 multi-chamber engine.

v_e 0 m/s

Sea Level • LOX/RP-1

RD-0120 Vac

Russian RD-0120 vacuum exhaust velocity. One of the highest chemical values.

v_e 0 m/s

Vacuum • LOX/LH₂

OMS Engine

Space Shuttle Orbital Maneuvering System. Hypergolic NTO/MMH.

v_e 0 m/s

Vacuum • NTO/MMH

AJ10

Aerojet AJ10 hypergolic engine. Apollo Service Module and Delta II upper stage.

v_e 0 m/s

Vacuum • NTO/Aerozine

Solid Rocket Booster

Space Shuttle / SLS SRB average exhaust velocity (APCP propellant).

v_e 0 m/s

Average • APCP

Solid Motor (Generic)

Typical APCP solid rocket motor exhaust velocity used on many launch vehicles.

v_e 0 m/s

APCP • Average

BE-3U

Blue Origin BE-3U upper-stage vacuum exhaust velocity.

v_e 0 m/s

Vacuum • LOX/LH₂

HM7B

Ariane 5 HM7B upper-stage exhaust velocity.

v_e 0 m/s

Vacuum • LOX/LH₂

Vulcain (Original)

Original Ariane 5 Vulcain sea-level exhaust velocity.

v_e 0 m/s

Sea Level • LOX/LH₂

RD-0120 SL

Russian RD-0120 sea-level exhaust velocity (Energia core).

v_e 0 m/s

Sea Level • LOX/LH₂

Castor 30

Orbital ATK Castor 30 solid motor vacuum exhaust velocity.

v_e 0 m/s

Vacuum • APCP

GEM-60

Graphite-Epoxy Motor (GEM-60) average exhaust velocity.

v_e 0 m/s

Average • APCP

Prometheus

ESA Prometheus reusable LOX/methane engine design exhaust velocity.

v_e 0 m/s

Sea Level • CH₄/LOX

NSTAR Ion

NASA NSTAR electrostatic xenon ion thruster (Deep Space 1 / Dawn).

v_e 0 m/s

Xenon Ion • Electric

Hall Thruster

Typical Hall-effect thruster exhaust velocity used on geostationary satellites.

v_e 0 m/s

Xenon Hall • Station-keeping

NEXT Ion

NASA NEXT ion thruster. Advanced electrostatic xenon thruster.

v_e 0 m/s

Xenon Ion • Electric

Hall SPT-100

Classic SPT-100 Hall-effect thruster exhaust velocity.

v_e 0 m/s

Xenon Hall

DS4G Ion

Dual-Stage 4-Grid electrostatic ion thruster concept. Extremely high exhaust velocity.

v_e 0 m/s

Xenon • Experimental

Nuclear Thermal

NERVA-class nuclear thermal rocket exhaust velocity with liquid hydrogen.

v_e 0 m/s

Nuclear • LH₂

Nuclear (Advanced)

Advanced nuclear thermal concepts with higher chamber temperature.

v_e 0 m/s

Nuclear Thermal • LH₂

VASIMR (High)

VASIMR high specific impulse mode. Variable plasma rocket exhaust velocity.

v_e 0 m/s

Plasma • High Isp Mode

VASIMR (Low)

VASIMR lower specific impulse / higher thrust mode.

v_e 0 m/s

Plasma • High Thrust Mode

Photonic (Ideal)

Theoretical pure photonic rocket (photon drive). Exhaust velocity = speed of light.

v_e 0 m/s

c • Theoretical

Hypergolic (Typical)

Typical storable hypergolic bipropellant exhaust velocity (NTO/MMH or similar).

v_e 0 m/s

Storable • Vacuum

LOX/LH₂ (Ideal Vac)

Near-ideal LOX/LH₂ vacuum exhaust velocity for high-expansion modern nozzles.

v_e 0 m/s

Ideal • LOX/LH₂ Vacuum

Ve Vector

Exit Speed. Exhaust Velocity is the measure of Propulsion Efficiency. It determines if a rocket can break gravity or reach the stars.

🔥 Chemical: High thrust, lower ve.
⚛️ Ion Drive: Low thrust, extreme ve.
📐 Nozzle: Shapes the gas to maximize exit speed.

🚀

🔥

💨

PROPULSION SCAN

VELOCITY 4.5km/s

SPECIFIC IMPULSE: 📈 HIGH

THRUST-SYNC ACTIVE ✅

I sp Metrics

Fuel Economy. Specific Impulse is the Time Dimension of thrust. It measures how long we can sustain push before the tank runs dry.

⏱️ Time: Higher seconds = more "bang for your buck."
⚖️ Gravity: To get velocity, multiply I sp by 9.8.
🌌 Distance: High I sp is the key to Mars and beyond.

⏱️

EFFICIENCY SCAN

450s

FUEL: ❄️ LIQUID HYDROGEN

IMPULSE-SYNC ACTIVE ✅

Vector G

Constant Pull. Gravity is the Invisible Tether. It defines how high we jump, how fast things fall, and the thickness of our atmosphere. 🌍📉⚖️

⚖️ Standard: 9.8m/s2 on Earth's surface.
🌑 Moon: Only 1.6 m/s2 (Floaty vibes).
⚛️ Force:F = m a (Mass times Gravity).

🍎

📉

GRAVIMETRIC SCAN

9.8 m/s²

PLANET: 🌍 EARTH-CORE

GRAVITY-SYNC ACTIVE ✅

Flow Rate

Propellant Throughput. Mass Flow is the Volume of Power. It defines how quickly you empty your tanks to fight against Earth's gravity.

🚰 The Valve: Controls how many kg/s enter the chamber.
⏲️ Burn Time: Higher mass flow = shorter total burn time.
🌋 Pressure: Created by the expansion of the flowing mass.

💧

🔥

💧

📟

THROUGHPUT SCAN

2,500 kg/s

PUMP STATUS: 🚀 MAX THRUST

FLOW-SYNC ACTIVE ✅

Ve Vector

The Performance Metric. Effective Velocity is the True Speed of the exhaust gas relative to the rocket. It is the heartbeat of deep-space travel.

🏁 Standard: Higher ve = Faster forward acceleration.
🧪 Chemistry: Different fuels provide different ve limits.
🌌 Deep Space: High ve is the only way to reach Mars efficiently.

🚀

⚡

PROPULSION EFFICIENCY

Ve: 4,400

UNIT: 🔭 m/s

VELOCITY-SYNC ACTIVE ✅

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