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@SkyPhoenix999
SkyPhoenix999 authored Apr 15, 2024
2 parents 362dc90 + 8fc1266 commit 8611d47
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76 changes: 75 additions & 1 deletion GameData/RealismOverhaul/Engine_Configs/AJ10_Adv_Config.cfg
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Expand Up @@ -49,8 +49,24 @@
// Nozzle Ratio: 65
// Ignitions: Infinite
// =================================================================================
// AJ10-133-Hylas
// Hylas
//
// Dry Mass: 81 kg larger nozzle, thinner ablative liner?
// Thrust (SL): ??? kN
// Thrust (Vac): 26.7 kN
// ISP: 1 @0.355 atm / 433 Vac SL calculated with RPA
// Burn Time: 450 "ablation essentially zero (...) for durations up to 300 sec". 1.5x?
// Chamber Pressure: 0.28 MPa
// Propellant: LOX / LH2
// Prop Ratio: 5.0
// Throttle: N/A
// Nozzle Ratio: 40
// Ignitions: 9? GE Apollo SPS had thicker ablative liner to support more restarts
// =================================================================================
// AJ10-133
// GE Apollo
// GE Apollo propulsion system used thrust chamber developed for Hylas, with shorter nozzle to fit on D-2
//
// Dry Mass: 81 Kg
// Thrust (SL): ??? kN
Expand All @@ -68,11 +84,17 @@
// Sources:

// Purdue Engineering - AJ10-118K: https://engineering.purdue.edu/~propulsi/propulsion/rockets/liquids/aj10-118k.html
// Aerojet General Space Engines: http://www.alternatewars.com/BBOW/Space_Engines/Aerojet_Engines.htm
// Aerojet General Space Engines: https://web.archive.org/web/20200229064124/http://www.alternatewars.com/BBOW/Space_Engines/Aerojet_Engines.htm
// Encyclopedia Astronautica - AJ10-118K: http://www.astronautix.com/engines/aj10118k.htm
// Aerojet Rocketdyne - AJ10-118K: https://www.rocket.com/delta-ii-stage-2-engine
// Norbert Brügge - US Space Rocket Engines: http://www.b14643.de/Spacerockets/Diverse/U.S._Rocket_engines/engines.htm
// Spaceflight 101 - Delta II 7920: http://spaceflight101.com/spacerockets/delta-ii-7920/
// https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=16154.0;attach=116872
// http://www.astronautix.com/t/thorhydra.html
// https://www.google.com/books/edition/Technical_Abstract_Bulletin/4SPJ4687C_AC?hl=en&gbpv=1&dq=AF+Contract+04(611)-5170&pg=RA2-PA189&printsec=frontcover
// https://www.holderaerospace.com/downloads/Technical_Papers/VaPak%20Systems%20Overview.pdf
// https://ntrs.nasa.gov/api/citations/19650010102/downloads/19650010102.pdf
// https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=30092.0;attach=467003
// A Historical Look at US Launch Vehicles.PDF

// Used by:
Expand Down Expand Up @@ -313,6 +335,57 @@
}
}

CONFIG
{
name = AJ10-133-Hylas
description = AJ10 variant burning liquid hydrogen and oxygen, proposed for use on the Hylas upper stage. Extremely low chamber pressure and autogeneous pressurization system allows conventional tanks to be used.
specLevel = prototype
minThrust = 26.67
maxThrust = 26.67
heatProduction = 100

PROPELLANT
{
name = LqdHydrogen
ratio = 0.7631
DrawGauge = True
}

PROPELLANT
{
name = LqdOxygen
ratio = 0.2369
}
//No pressurant, used "VaPak" autogeneous pressurization system

ullage = True
pressureFed = False //At 40 psi chamber pressure, this could use mostly normal tanks
ignitions = 9

IGNITOR_RESOURCE
{
name = ElectricCharge
amount = 0.2
}

atmosphereCurve
{
key = 0 433
key = 0.355 1
}

massMult = 0.81

TESTFLIGHT:NEEDS[TestLite|TestFlight]
{
ratedBurnTime = 450
ignitionReliabilityStart = 0.96
ignitionReliabilityEnd = 0.9965
cycleReliabilityStart = 0.94
cycleReliabilityEnd = 0.998 //Reliable but not incredibly so 4 were used for a reason
}
}

CONFIG
{
name = AJ10-133-LH
Expand Down Expand Up @@ -367,6 +440,7 @@
ignitionReliabilityEnd = 0.9965
cycleReliabilityStart = 0.94
cycleReliabilityEnd = 0.998 //Reliable but not incredibly so 4 were used for a reason
techTransfer = AJ10-133-Hylas:50
}
}
}
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16 changes: 16 additions & 0 deletions GameData/RealismOverhaul/Engine_Configs/EngineVariants_Config.cfg
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Expand Up @@ -14,13 +14,21 @@
@cost *= #$../../engineTypeMult$
@minThrust *= #$../../engineTypeMult$
@maxThrust *= #$../../engineTypeMult$
@dryThrust *= #$../../engineTypeMult$
@wetThrust *= #$../../engineTypeMult$
@thrustUpperLimit *= #$../../engineTypeMult$
@Area *= #$../../engineTypeMult$
@thrusterPower *= #$../../engineTypeMult$
@SUBCONFIG,*
{
@cost *= #$../../../engineTypeMult$
@costOffset *= #$../../../engineTypeMult$
@minThrust *= #$../../../engineTypeMult$
@maxThrust *= #$../../../engineTypeMult$
@dryThrust *= #$../../../engineTypeMult$
@wetThrust *= #$../../../engineTypeMult$
@thrustUpperLimit *= #$../../../engineTypeMult$
@Area *= #$../../../engineTypeMult$
@thrusterPower *= #$../../../engineTypeMult$
}
}
Expand All @@ -43,13 +51,21 @@
@cost *= #$../../engineTypeMult$
@minThrust *= #$../../minActiveEngines$
@maxThrust *= #$../../engineTypeMult$
@dryThrust *= #$../../engineTypeMult$
@wetThrust *= #$../../engineTypeMult$
@thrustUpperLimit *= #$../../engineTypeMult$
@Area *= #$../../engineTypeMult$
@thrusterPower *= #$../../engineTypeMult$
@SUBCONFIG,*
{
@cost *= #$../../../engineTypeMult$
@costOffset *= #$../../../engineTypeMult$
@minThrust *= #$../../../minActiveEngines$
@maxThrust *= #$../../../engineTypeMult$
@dryThrust *= #$../../../engineTypeMult$
@wetThrust *= #$../../../engineTypeMult$
@thrustUpperLimit *= #$../../../engineTypeMult$
@Area *= #$../../../engineTypeMult$
@thrusterPower *= #$../../../engineTypeMult$
}
}
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64 changes: 63 additions & 1 deletion GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/J57_Config.cfg
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Expand Up @@ -151,13 +151,37 @@
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// J57-P-420
// 1967, F-8H/J, RF-8G
//
// Dry Mass: 2195 kg
// Thrust (Dry): 55.2 kN
// Thrust (Wet): 87.2 kN
// SFC (Dry): 0.87 lb/lbf-hr
// Area: 0.24 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 13.0 //Compressor Pressure Ratio
// FPR: 0.0 //Fan Ratio
// Mdes: 0.9 M //Mach Design Point
// Tdes: 250 K //Temp Design Point
// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance
// FHV: 35000000 J //Fuel heat of burning
// TIT: 1330 K //Combustion peak temp
// TAB: 2556* K //Afterburner peak temp
// maxT3: 825 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================

// Sources:

// https://www.jet-engine.net/miltfspec.htm
// https://en.wikipedia.org/wiki/Pratt_%26_Whitney_J57
// https://www.thisdayinaviation.com/tag/pratt-whitney-jt3c-6/
// https://aircorpslibrary.com/jt3c-4-and-jt3c-6/
// https://www.marvellouswings.com/Aircraft/Fighter/F-8/F-8.html
// https://www.aerosociety.com/media/8037/an-examination-of-the-f-8-crusader-through-archival-sources.pdf
// https://www.tapatalk.com/groups/warships1discussionboards/if-no-phantom-upgrade-what-to-operate-from-audacio-t31193.html

// Used by:

Expand Down Expand Up @@ -519,7 +543,7 @@
CONFIG
{
name = J57-P-20A
description = Ultimate afterburning J57, as used on the F-8E/J. Temperature Mach limit at 15 km: 2.5.
description = Afterburning J57, as used on the F-8E/J. Temperature Mach limit at 15 km: 2.5.
massMult = 1.00

Area = 0.24 //Compressor Area
Expand Down Expand Up @@ -547,6 +571,44 @@
drySFC = 0.77
throttleResponseMultiplier = 0.3 //60s double-spool, 0.3

PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = J57-P-420
description = Ultimate afterburning J57, remanufactured J57-P-20 as used on upgraded F-8H/J. Temperature Mach limit at 15 km: 2.58.
massMult = 1.0186

Area = 0.24 //Compressor Area
BPR = 0 //Bypass Ratio
CPR = 13.0 //Compressor Pressure Ratio
FPR = 0 //Fan Ratio
Mdes = 0.9 //Mach Design Point
Tdes = 250 //Temp Design Point
eta_c = 0.95 //Efficiency at burner inlet
eta_t = 0.98 //Efficiency at burner exit
eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance
FHV = 35000000 //Fuel heat of burning (joules?)
TIT = 1330 //Combustion peak temp
TAB = 2556 //Afterburner temp?
maxT3 = 850 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 170

// Engine fitting params
defaultTPR = 0.85
dryThrust = 55.2
wetThrust = 87.2
maxThrust = 87.2 //Just to let MEC know thrust
drySFC = 0.87
throttleResponseMultiplier = 0.3 //60s double-spool, 0.3

PROPELLANT
{
name = Kerosene
Expand Down
67 changes: 64 additions & 3 deletions GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/J79_Config.cfg
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Expand Up @@ -198,7 +198,7 @@
//
// Dry Mass: 1745 kg
// Thrust (Dry): 53.60 kN
// Thrust (Wet): 82.29 kN
// Thrust (Wet): 83.29 kN
// SFC (Dry): 0.834 lb/lbf-hr
// Area: 0.29 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
Expand All @@ -214,11 +214,33 @@
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// J79-IAI-J1E
// 1982, Kfir C.7
//
// Dry Mass: 1740? kg
// Thrust (Dry): 49.4 kN
// Thrust (Wet): 83.4 kN
// SFC (Dry): 0.843? lb/lbf-hr
// Area: 0.29 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 12.2 //Compressor Pressure Ratio
// FPR: 0.0 //Fan Ratio
// Mdes: 0.9 M //Mach Design Point
// Tdes: 250 K //Temp Design Point
// eta_n: 0.7 //Efficiency at afterburner rear / nozzle entrance
// FHV: 28000000 J //Fuel heat of burning
// TIT: 1261? K //Combustion peak temp
// TAB: 2767* K //Afterburner peak temp
// maxT3: 850 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================

// Sources:

// http://www.leteckemotory.cz/motory/j79/
// https://www.jet-engine.net/miltfspec.htm
// http://paulcegelski.com/j79.html

// Used by:

Expand Down Expand Up @@ -641,11 +663,50 @@
// Engine fitting params
defaultTPR = 0.85
dryThrust = 53.60
wetThrust = 82.29
maxThrust = 82.29 //Just to let MEC know thrust
wetThrust = 83.29
maxThrust = 83.29 //Just to let MEC know thrust
drySFC = 0.834
throttleResponseMultiplier = 0.60

PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = J79-IAI-J1E
description = License-built J79, created by IAI for the Kfir C.7. Temperature Mach limit at 15 km: 2.75.
specLevel = operational
massMult = 1.1538

Area = 0.29 //Compressor Area
BPR = 0.0 //Bypass Ratio
CPR = 12.2 //Compressor Pressure Ratio
FPR = 0.0 //Fan Ratio
Mdes = 0.9 //Mach Design Point
Tdes = 250 //Temp Design Point
eta_c = 0.95 //Efficiency at burner inlet
eta_t = 0.98 //Efficiency at burner exit
eta_n = 0.7 //Efficiency at afterburner rear / nozzle entrance
FHV = 28000000 //Fuel heat of burning (joules?)
TIT = 1261 //Combustion peak temp
TAB = 2767 //Afterburner temp?
maxT3 = 850 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 160

// Engine fitting params
defaultTPR = 0.85
dryThrust = 49.4
wetThrust = 83.4
maxThrust = 83.4 //Just to let MEC know thrust
drySFC = 0.843
throttleResponseMultiplier = 0.60

PROPELLANT
{
name = Kerosene
Expand Down
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