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Difference between revisions of "Rocket Engines"

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(Updated values based on in-game wiki and testing)
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   {| class="wikitable sortable" style="width:100%;"
 
   {| class="wikitable sortable" style="width:100%;"
 
     ! rowspan=2 | Name
 
     ! rowspan=2 | Name
−
     ! rowspan=2 | Base Power Usage
+
     ! rowspan=2 | Power Usage, W
−
     ! rowspan=2 | Rocket Mass Contribution
+
     ! rowspan=2 | Rocket Mass Contribution, kg
−
     ! rowspan=2 | Max Thrust
+
     ! rowspan=2 | Formal Max Thrust, kN
−
     ! colspan=2 | Real Max Thrust
+
     ! colspan=2 | Tested Max Thrust, kN
−
     ! rowspan=2 | Efficiency
+
    ! colspan=2 | Propellant consumption<ref>Consumption values were measured for "Tested Max Thrust", maximum efficiency.</ref>, mol/tick
−
     ! rowspan=2 | Exhaust Velocity
+
     ! rowspan=2 | Efficiency, %
 +
     ! rowspan=2 | Exhaust Velocity, km/s
 +
    ! rowspan=2 | Specifc Index I<sub>sp</sub>, s
 
     |-
 
     |-
  
−
     ! Using O2
+
     ! Using O<sub>2</sub>
−
     ! Using N2O
+
     ! Using N<sub>2</sub>O
 +
    ! Using O<sub>2</sub>
 +
    ! Using N<sub>2</sub>O
 +
    |-
 +
 
 +
    ! <b>[[Pumped Gas Engine]]</b>
 +
    | 200
 +
    | 500
 +
    | 16.20
 +
    | 16.54
 +
    | 24.47
 +
    | 18.00
 +
    | 18.00
 +
    | 100
 +
    | 4.02
 +
    | 411
 +
    |-
 +
 
 +
    ! <b>[[Pumped Liquid Engine]]</b>
 +
    | 200
 +
    | 500
 +
    | 17.90
 +
    | 18.74<ref name="PLE-CE">Cooling fuel lower than barely condensing temperatures gives minor upside on engine thrust, <1% increase</ref>
 +
    | 31.25<ref name="PLE-CE"/>
 +
    | 15.00
 +
    | 16.<span style="border-top: 1px solid">66</span>
 +
    | 140
 +
    | 5.56
 +
    | 568
 
     |-
 
     |-
  
 
     ! <b>[[Pressure Fed Gas Engine]]</b>
 
     ! <b>[[Pressure Fed Gas Engine]]</b>
−
     | 10W
+
     | 10
−
     | 500kg
+
     | 500
−
     | 40.3kN
+
     | 40.30
−
     | 59.9kN
+
     | 60.32
−
     | 41.9kN<ref>N2O must be much hotter to avoid condensing therefore decreasing pumping rate</ref>
+
     | 41.57
−
     | 96%
+
    | 69.77
−
     | 3.86km/s (Isp: 394s)
+
    | 31.68<ref name="NitroPumpRate">N<sub>2</sub>O temperature must be above max condensing point to allow high pressures, therefore decreasing pumping rate.</ref>
 +
     | 96
 +
     | 3.86
 +
    | 394
 
     |-
 
     |-
  
−
     ! <b>[[Pumped Gas Engine]]</b>
+
     ! <b>[[Pressure Fed Liquid Engine]]</b>
−
     | 200W
+
     | 20
−
     | 500kg
+
     | 500
−
     | 16.2kN
+
     | 29.30
−
     | 16.3kN
+
    | 38.84
−
     | 24.4kN
+
    | 59.70
−
     | 100%
+
     | 27.23
−
     | 4.02km/s (Isp: 411s)
+
     | 28.16
 +
     | 160
 +
     | 6.31
 +
    | 644
 
     |-
 
     |-
  
−
     ! <b>[[Pumped Liquid Engine]]</b>
+
     ! <b>[[Heavy Pressure Fed Gas Engine]]</b>
−
     | 200W
+
     | 10
−
     | 500kg
+
     | 750
−
     | 17.9kN
+
     | 62.60
−
     | 18.7kN
+
     | 93.87
−
     | 31.3kN
+
     | 64.75
−
     | 140%
+
     | 118.45
−
     | 5.56km/s (Isp: 568s)
+
     | 53.83<ref name="NitroPumpRate" />
 +
    | 88
 +
    | 3.54
 +
    | 361
 
     |-
 
     |-
  
−
     ! <b>[[Pressure Fed Liquid Engine]]</b>
+
     ! <b>[[Heavy Pressure Fed Liquid Engine]]</b>
−
     | 20W
+
     | 20
−
     | 500kg
+
     | 750
−
     | 29.3kN
+
     | 44.30
−
     | 38kN
+
     | 60.39
−
     | 58.7kN
+
     | 95.52
−
     | 160%
+
     | 47.03
−
     | 6.31km/s (Isp: 644s)
+
     | 49.86
 +
    | 144
 +
    | 5.68
 +
    | 579
 
     |-
 
     |-
  
−
     ! colspan=8 | <i>Update 0.2.6091.26702 - 01/17/2026</i> <span class="right">[[Rocket_Engines]]</span>
+
     ! colspan=11 | <i>Update 0.2.6136.26812 - 01/28/2026</i> <span class="right">[[Rocket_Engines]]</span>
 
   |}
 
   |}
 
</div>
 
</div>

Revision as of 19:18, 15 February 2026


Rocket Engines give you their max output in kN with this you can calculate what they can reasonably carry into orbit depending on the planet or moon you are on. Force = Mass * Acceleration. Acceleration is equal to the planet's gravity, Mass is given in kg per part of the rocket, and Force is kN. If your thrust force listed below is less than the weight of the rocket in kN then you will not even take off. It is better to have a thrust much higher than the weight of the rocket or else you risk running out of fuel on launch and on landing.

Liquid propellants bring greater efficiencies. Using Nitrous Oxide as oxidizer provides excessive thrust values. Keep in mind that N2O fuel mix is 1.9375 times heavier at same moles, or 2.15 times heavier at same volume, while thrust boost is around 1.5-1.7. Engine efficiency determines "bonus" thrust multiplier, meaning engine with higher efficiency will give more thrust consuming same amount of fuel. Thus using liquid engines is more favorable if one can cool fuel down, moreover Pressure Fed Engines consume fuel inversely proportional to its temperature. On the other hand if Volatiles and Oxygen are in excess (e.g. farm on Vulcan) is may be much easier to opt for Pressure Fed Gas Engine. It will provide ~40kN at 20°C.

Name Power Usage, W Rocket Mass Contribution, kg Formal Max Thrust, kN Tested Max Thrust, kN Propellant consumption[1], mol/tick Efficiency, % Exhaust Velocity, km/s Specifc Index Isp, s
Using O2 Using N2O Using O2 Using N2O
Pumped Gas Engine 200 500 16.20 16.54 24.47 18.00 18.00 100 4.02 411
Pumped Liquid Engine 200 500 17.90 18.74[2] 31.25[2] 15.00 16.66 140 5.56 568
Pressure Fed Gas Engine 10 500 40.30 60.32 41.57 69.77 31.68[3] 96 3.86 394
Pressure Fed Liquid Engine 20 500 29.30 38.84 59.70 27.23 28.16 160 6.31 644
Heavy Pressure Fed Gas Engine 10 750 62.60 93.87 64.75 118.45 53.83[3] 88 3.54 361
Heavy Pressure Fed Liquid Engine 20 750 44.30 60.39 95.52 47.03 49.86 144 5.68 579
Update 0.2.6136.26812 - 01/28/2026 Rocket_Engines
  1. ↑ Consumption values were measured for "Tested Max Thrust", maximum efficiency.
  2. ↑ 2.0 2.1 Cooling fuel lower than barely condensing temperatures gives minor upside on engine thrust, <1% increase
  3. ↑ 3.0 3.1 N2O temperature must be above max condensing point to allow high pressures, therefore decreasing pumping rate.
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