Difference between revisions of "CR-7 R.A.P.I.E.R. Engine/Box"

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m (*update to 0.24.2;)
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|role={{lang|en=Hybrid engine|pl=Silnik hybrydowy}}
 
|role={{lang|en=Hybrid engine|pl=Silnik hybrydowy}}
 
|size=s
 
|size=s
|manufacturer=C7 Aerospace Division
+
|manufacturer=C7
|manufacturer2=Rockomax Conglomerate
+
|manufacturer2=RMC
|costs=3600
+
|costs=6000
|mass=1.2
+
|mass=2.0
 
|drag=0.2
 
|drag=0.2
|temp=3600
+
|temp=2000
 
|tolerance=20
 
|tolerance=20
|research=Hypersonic Flight
+
|research=Aerospace Tech
 +
|unlock cost=35000
 
|since=0.23
 
|since=0.23
 +
|filename=rapierEngine.cfg
 
|part=rapierEngine
 
|part=rapierEngine
 
|parent=Engine
 
|parent=Engine
|more=
+
|more={{Infobox/Part/title|lfe}}
{{Infobox/Part/title|lfe}}
 
 
{{Infobox/Part/reaction engine
 
{{Infobox/Part/reaction engine
|thrust=175
+
|fuel=lfox
|isp-atm=320
+
|isp-atm=275
|isp-vac=360
+
|isp-vac=305
 +
|thrust=180
 
|vectoring=3
 
|vectoring=3
 
}}
 
}}
 
{{Infobox/Part/title|je}}
 
{{Infobox/Part/title|je}}
{{Infobox/Part/JetEngine
+
{{Infobox/Part/jet engine
|thrust=190
+
|intake=6 <!-- Amount of Air required per 1 unit of LF (Calc: Air / LF) -->
|stall=63 (?)
+
|isp=3200
|isp=800
+
|thrust=105
 
|vectoring=3
 
|vectoring=3
 +
}}
 +
{{Infobox/Part/test subject
 +
|environments=127
 +
|event=True
 +
|staging=True
 
}}
 
}}
 
}}
 
}}

Latest revision as of 16:25, 18 August 2018

This is a data template. To add content which doesn't belong to this template edit the English page (or one of its translations).
CR-7 R.A.P.I.E.R. Engine
Part image
Hybrid engine by
C7 Aerospace Divisionand Rockomax Conglomerate

Radial size Small
Cost (total) 6 000.00 Funds
Mass (total) 2.00 t
Drag 0.2
Max. Temp. 2000 K
Volume  ?
Impact Tolerance 20 m/s
Research Aerospace tech.png Aerospace Tech
Unlock cost 35 000 Funds
Since version 0.23
Part configuration rapierEngine.cfg
Liquid fuel engine
Maximum thrust (1 atm) 162.30 kN
(vacuum) 180.00 kN
Isp (1 atm) 275 s
(vacuum) 305 s
Fuel consumption 12.04 Units of fuel/s


Thrust vectoring 3 °
Jet engine
Maximum thrust 105 kN
Isp (max) 3200 s
Fuel consumption 0.67 Units of fuel/s
Intake air consumption 4.02 Air unit/s
Thrust vectoring 3 °
Testing Environments
On the surface Yes
In the ocean Yes
On the launchpad Yes
In the atmosphere Yes
Sub orbital Yes
In an orbit Yes
On an escape Yes
Docked No
Test by staging Yes
Manually testable Yes