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Chinese engine configs (+Kerwis) (#2932)
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* Long March 1

* Long March 2

* Long March 3

* Long March 5

* kerwis compat

---------

Co-authored-by: NovemberOrWhatever <willtreatyr.50@gmail.com>
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@Capkirk123 @NovemberOrWhatever
Capkirk123 and NovemberOrWhatever authored Jan 29, 2024
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249 changes: 248 additions & 1 deletion GameData/RealismOverhaul/Engine_Configs/Jet_Engine_Configs/R11_Config.cfg
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Original file line number Diff line number Diff line change
Expand Up @@ -67,11 +67,102 @@
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// WP-7
// 1966, J-7
//
// Dry Mass: 1151 kg
// Thrust (Dry): 38.25 kN
// Thrust (Wet): 56.39 kN
// SFC (Dry): 0.989 lb/lbf-hr
// Area: 0.25 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 8.85 //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: 30000000 J //Fuel heat of burning
// TIT: 1188 K //Combustion peak temp temperature increased by 100 C
// TAB: 1988* K //Afterburner peak temp
// maxT3: 750 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// WP-7A
// 1969, J-8
//
// Dry Mass: 1158 kg
// Thrust (Dry): 43.15 kN
// Thrust (Wet): 58.84 kN
// SFC (Dry): 0.997 lb/lbf-hr
// Area: 0.25 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 8.85 //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: 30000000 J //Fuel heat of burning
// TIT: 1288 K //Combustion peak temp temperature increased by 100 C
// TAB: 1844* K //Afterburner peak temp
// maxT3: 750 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// WP-7B
// 1978, J-7/IIM, JJ-7, F-7BK/M, J-8I
//
// Dry Mass: 1191 kg
// Thrust (Dry): 43.15 kN
// Thrust (Wet): 59.82 kN
// SFC (Dry): 1.03 lb/lbf-hr
// Area: 0.25 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 8.85 //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: 30000000 J //Fuel heat of burning
// TIT: 1288 K //Combustion peak temp
// TAB: 1906* K //Afterburner peak temp
// maxT3: 750 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================
// WP-7BM? (a.k.a. WP-7C?, WP-7BB?)
// 1982, J-7I/II/IIH, F-7A/B
//
// Dry Mass: 1174 kg weight reduced by 17 kg
// Thrust (Dry): 43.15 kN
// Thrust (Wet): 60.60 kN
// SFC (Dry): 1.014 lb/lbf-hr 1.5% improved fuel consumption?
// Area: 0.25 m^2 //Compressor Area
// BPR: 0.0 //Bypass Ratio
// CPR: 8.85 //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: 30000000 J //Fuel heat of burning
// TIT: 1288 K //Combustion peak temp
// TAB: 1956* K //Afterburner peak temp
// maxT3: 800 K //Turbine max temperature
// Exhaust Mixer: false
// Adjustable Nozzle: true
// =================================================================================

// Sources:

// http://www.leteckemotory.cz/motory/r-11/
// https://www.jet-engine.net/miltfspec.htm
// https://en.wikipedia.org/wiki/List_of_Chengdu_J-7_variants
// https://zh.wikipedia.org/wiki/%E6%AD%BC-7
// https://www.globalsecurity.org/military/world/china/wp7b.htm
// https://baike.baidu.com/item/%E6%B6%A1%E5%96%B7-7/3320215
// https://www.toutiao.com/article/7279380979536888374/?wid=1702343967612
// https://www.bilibili.com/read/cv12544738/
// Aviation World 2015.1 - The Heroic Heart - A brief discussion of China's military aviation engines
// Used by:
Expand All @@ -85,7 +176,7 @@
%manufacturer = #roMfrOKB300
%description = #roR11Desc
@tags ^= :$: ussr okb300 r11 r-11 afterburning turbojet
@tags ^= :$: ussr prc china okb300 r11 r-11 wp7 wp-7 afterburning turbojet
%specLevel = operational //operational, prototype, concept, speculative, altHist, sciFi
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drySFC = 0.95
throttleResponseMultiplier = 0.30 //60s double-spool, 0.30
PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = WP-7
description = Afterburning R-11 derivative, as used on the J-7. Temperature Mach limit at 15 km: 2.54.
specLevel = operational
massMult = 1.004
Area = 0.25 //Compressor Area
BPR = 0.0 //Bypass Ratio
CPR = 8.85 //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 = 30000000 //Fuel heat of burning (joules?)
TIT = 1188 //Combustion peak temp
TAB = 1988 //Afterburner temp?
maxT3 = 750 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 120
// Engine fitting params
defaultTPR = 0.85
dryThrust = 38.25
wetThrust = 56.39
maxThrust = 56.39 //Just to let MEC know thrust
drySFC = 0.989
throttleResponseMultiplier = 0.30 //60s 2-spool/variable vanes: 0.30
PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = WP-7A
description = Afterburning R-11 derivative, as used on the J-8. Temperature Mach limit at 15 km: 2.54.
specLevel = operational
massMult = 1.010
Area = 0.25 //Compressor Area
BPR = 0.0 //Bypass Ratio
CPR = 8.85 //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 = 30000000 //Fuel heat of burning (joules?)
TIT = 1288 //Combustion peak temp
TAB = 1844 //Afterburner temp?
maxT3 = 750 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 120
// Engine fitting params
defaultTPR = 0.85
dryThrust = 43.15
wetThrust = 58.84
maxThrust = 58.84 //Just to let MEC know thrust
drySFC = 0.997
throttleResponseMultiplier = 0.30 //60s 2-spool/variable vanes: 0.30
PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = WP-7B
description = Afterburning R-11 derivative, as used on the J-7IIM, JJ-7, F-7BK/M and J-8I. Temperature Mach limit at 15 km: 2.54.
specLevel = operational
massMult = 1.039
Area = 0.25 //Compressor Area
BPR = 0.0 //Bypass Ratio
CPR = 8.85 //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 = 30000000 //Fuel heat of burning (joules?)
TIT = 1288 //Combustion peak temp
TAB = 1906 //Afterburner temp?
maxT3 = 750 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 120
// Engine fitting params
defaultTPR = 0.85
dryThrust = 43.15
wetThrust = 59.82
maxThrust = 59.82 //Just to let MEC know thrust
drySFC = 1.03
throttleResponseMultiplier = 0.60 //70s: 0.60
PROPELLANT
{
name = Kerosene
ratio = 1.0
DrawGauge = True
}
}
CONFIG
{
name = WP-7BM
description = Afterburning R-11 derivative, as used on the J-7IIH and F-7A/B. Temperature Mach limit at 15 km: 2.77.
specLevel = operational
massMult = 1.024
Area = 0.25 //Compressor Area
BPR = 0.0 //Bypass Ratio
CPR = 8.85 //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 = 30000000 //Fuel heat of burning (joules?)
TIT = 1288 //Combustion peak temp
TAB = 1956 //Afterburner temp?
maxT3 = 800 //Turbine max temperature
exhaustMixer = False
adjustableNozzle = True
thrustUpperLimit = 120
// Engine fitting params
defaultTPR = 0.85
dryThrust = 43.15
wetThrust = 60.60
maxThrust = 60.60 //Just to let MEC know thrust
drySFC = 1.014
throttleResponseMultiplier = 0.80
PROPELLANT
{
name = Kerosene
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