Config cleanup and some more improvements

GameData/RealismOverhaul/Engine_Configs/18KS7800_Config.cfg

@@ -10,7 +10,7 @@
 //	Dry Mass: 27.21 Kg
 //	Thrust (SL): ??? kN
 //	Thrust (Vac): 34.09 kN
-//	ISP: ??? SL / 238.8 Vac
+//	ISP: 200? SL / 238.8 Vac
 //	Burn Time: 1.8
 //	Chamber Pressure: 6.89 MPa
 //	Propellant: NGNC

GameData/RealismOverhaul/Engine_Configs/25KS18000_Config.cfg

@@ -10,7 +10,7 @@
 //	Dry Mass: 117.9 Kg
 //	Thrust (SL): 82.7 kN
 //	Thrust (Vac): ??? kN
-//	ISP: 178 SL / ??? Vac
+//	ISP: 178 SL / 198.8? Vac
 //	Burn Time: 2.5
 //	Chamber Pressure: 9.24 MPa
 //	Propellant: NGNC

GameData/RealismOverhaul/Engine_Configs/A-4_Config.cfg

@@ -27,7 +27,7 @@
 //	Thrust (Vac): 288.68 kN
 //	ISP: 220 SL / 255 Vac
 //	Burn Time: 115
-//	Chamber Pressure: ??? MPa
+//	Chamber Pressure: 1.7? MPa	estimated with RPA
 //	Propellant: LOX / Hydyne
 //	Prop Ratio: 1.3253, same as A-6H?
 //	Throttle: N/A

GameData/RealismOverhaul/Engine_Configs/AJ10_Early_Config.cfg

@@ -9,7 +9,7 @@
 //
 //	Dry Mass: 84 Kg
 //	Thrust (SL): ??? kN
-//	Thrust (Vac): 35.585 kN
+//	Thrust (Vac): 33.8 kN
 //	ISP: 122 SL / 271 Vac		SL calculated with RPA
 //	Burn Time: 115
 //	Chamber Pressure: 1.4 MPa

GameData/RealismOverhaul/Engine_Configs/AJ260FL_Config.cfg

@@ -1,29 +1,41 @@
+//	==================================================
 //	AJ-260 FL
-//	Bluedog_DB
 //
 //	Manufacturer: Aerojet
+//
 //	=================================================================================
 //	AJ-260 FL
-//	30.48 x 6.63448 m
+
 //	Dry Mass: 156,126 kg
-//	Thrust: 35,391 kN Vac
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 35,391 kN
 //	ISP: 238 SL / 263 Vac
 //	Web Burn Time: 114 s
 //	Total Burn Time: 130 s
+//	Chamber Pressure: 4.15 MPa
 //	Propellant: PBAN
-//	Propellant Weight: 1,492,229 kg
-//	Nozzle Diameter: 181 in
-//	Nozzle Expansion Ratio: 3.8:1
-//	Nozzle Exit Area:
+//	Throttle: N/A
+//	Nozzle Ratio: 3.8:1
+//	Ignitions: 1
 //	=================================================================================
 
-//	SOURCES
+//	Sources:
+
 //	#1: NASA CR-72127 - 260-in. Diameter Motor Deasibility Demonstration Program: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670005578.pdf
 //	#2: NASA TM X-1906 - Thrust Vector Control Requirements for Launch Vehicles using a 260-inch Solid Rocket First Stage (1969): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700003019.pdf
 //	#3: Test of 260-Inch Diameter Motor SL-3: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680025253.pdf
-//
-//	=================================================================================
 
+//	Used by:
+
+//	* BDB
+//	* ROEngines
+
+//	Notes:
+
+//	30.48 x 6.63448 m
+//	Propellant Weight: 1,492,229 kg
+//	Nozzle Diameter: 181 in
+//	==================================================
 @PART[*]:HAS[#engineType[AJ260FL]]:FOR[RealismOverhaulEngines]
 {
 	%title = #roAJ260FLTitle	//AJ-260 FL

GameData/RealismOverhaul/Engine_Configs/AJ260SL_Config.cfg

@@ -1,38 +1,57 @@
+//	==================================================
 //	AJ-260 SL
-//	Bluedog_DB
 //
 //	Manufacturer: Aerojet
+//
 //	=================================================================================
 //	AJ-260 SL-1/2 (Short Length)
-//	80 ft, 9 in x 261.2 in = 21.6126 x 6.63448 m
+
 //	Dry Mass: 181,935 lb = 82,524.26 kg
 //	Liquid Injection Thrust Vector = 6650 kg added
 //	Total Dry Mass: 89,174.26 kg
-//	Thrust: 3,567,000 lbf = 15,866.8 kN
-//	Total Impulse: 371,900,000 lb s
+//	Thrust (SL): 3,567,000 lbf = 15,866.8 kN
+//	Thrust (Vac): ??? kN
 //	Web Burn Time: 114 s
 //	Total Burn Time: 130 s
-//	Chamber Pressure: 602 psia (max)
+//	Chamber Pressure: 4.15 MPa (max)
 //	Propellant: PBAN
-//	Propellant Weight: 1,676,366 lb = 760,386 kg
-//	Nozzle Diameter: 181 in
+//	Throttle: N/A
 //	Nozzle Expansion Ratio: 3.8:1
-//	Nozzle Exit Area:
+//	Ignitions: 1
 //	=================================================================================
 //	AJ-260 SL-3
-//	Thrust: 5,370,000 lbf = 23,886.941 kN
+
+//	Dry Mass: 181,935 lb = 82,524.26 kg
+//	Liquid Injection Thrust Vector = 6650 kg added
+//	Total Dry Mass: 89,174.26 kg
+//	Thrust (SL): 5,370,000 lbf = 23,886.941 kN
+//	Thrust (Vac): ??? kN
 //	Web Burn Time: 75.2 s
-//	Total Burn Time: 
+//	Total Burn Time: ???
+//	Chamber Pressure: 4.14 MPa (max)
+//	Propellant: PBAN
+//	Throttle: N/A
 //	Nozzle Area Ratio: 3.78
+//	Ignitions: 1
 //	=================================================================================
-//
-//	SOURCES
+
+//	Sources:
+
 //	#1: NASA CR-72127 - 260-in. Diameter Motor Deasibility Demonstration Program: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670005578.pdf
 //	#2: NASA TM X-1906 - Thrust Vector Control Requirements for Launch Vehicles using a 260-inch Solid Rocket First Stage (1969): https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700003019.pdf
 //	#3: Test of 260-Inch Diameter Motor SL-3: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680025253.pdf
-//
-//	=================================================================================
 
+//	Used by:
+
+//	* BDB
+//	* ROEngines
+
+//	Notes:
+
+//	80 ft, 9 in x 261.2 in = 21.6126 x 6.63448 m
+//	Propellant Weight: 1,676,366 lb = 760,386 kg
+//	Nozzle Diameter: 181 in
+//	==================================================
 @PART[*]:HAS[#engineType[AJ260SL]]:FOR[RealismOverhaulEngines]
 {
 	%title = #roAJ260SLTitle	//AJ-260 SL

GameData/RealismOverhaul/Engine_Configs/AR1_Config.cfg

@@ -12,13 +12,11 @@
 //	Thrust (Vac): 2487 kN
 //	ISP: 305 SL / 337 Vac
 //	Burn Time: 450
-//	Chamber Pressure: ??? MPa
+//	Chamber Pressure: 26.66 MPa		same as RD-180???
 //	Propellant: LOX / RP-1
-//	Prop Ratio: 2.72 from the RD-180???
-//	Engine Nozzle: ???
-//	Nozzle Exit Area: ???
+//	Prop Ratio: 2.72		same as RD-180???
 //	Throttle: 100% to 50%
-//	Nozzle Ratio: ???
+//	Nozzle Ratio: 36.87		same as RD-180???
 //	Ignitions: 1
 //	=================================================================================
 

GameData/RealismOverhaul/Engine_Configs/Aestus_Config.cfg

@@ -12,7 +12,7 @@
 //	Thrust (Vac): 27.8 kN
 //	ISP: 113 SL / 306 Vac
 //	Burn Time: 1110
-//	Chamber Pressure: 1.1
+//	Chamber Pressure: 1.1 MPa
 //	Propellant: MON3 / MMH	designed in the 90s, probably MON3
 //	Prop Ratio: 1.9
 //	Throttle: N/A

GameData/RealismOverhaul/Engine_Configs/Agena_XLR81_Config.cfg

@@ -7,7 +7,7 @@
 //	Model 117
 //	B-58 Hustler rocket pod
 //
-//	Dry Mass: 127 Kg
+//	Dry Mass: 114.3 Kg	a little lighter, because no Gimbal
 //	Thrust (SL): ??? kN
 //	Thrust (Vac): 67 kN
 //	ISP: 207 SL / 265.5 Vac		SL calculated with RPA
@@ -247,6 +247,7 @@
 			minThrust = 67
 			heatProduction = 100
 			gimbalRange = 0
+			massMult = 0.9
 			PROPELLANT
 			{
 				name = Kerosene

GameData/RealismOverhaul/Engine_Configs/Algol_III_Config.cfg

@@ -4,15 +4,15 @@
 //	Manufacturer: Aerojet
 //
 //	=================================================================================
-//	Algol III
+//	Algol IIIA
 //	Scout
 //
 //	Dry Mass: 1391.121 kg
 //	Thrust (SL): ??? kN
 //	Thrust (Vac): 530.25896 kN
 //	ISP: 238 SL / 260.289 Vac
 //	Burn Time: 70
-//	Chamber Pressure: ??? MPa
+//	Chamber Pressure: 6.69 MPa
 //	Propellant: PBAN
 //	Prop Ratio: N/A
 //	Throttle: N/A
@@ -23,6 +23,7 @@
 //	Sources:
 
 //	NASA CR-165950 Scout Launch Vehicle Final Report.PDF
+//	https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf
 
 //	Used by:
 

GameData/RealismOverhaul/Engine_Configs/AltairIII_Config.cfg

@@ -1,25 +1,39 @@
-//	===============================================================
-//
-//	Altair III (FW4S) SRM
-//	Squad, Bluedog_DB
+//	==================================================
+//	Altair III (FW4S)
 //
 //	Manufacturer: United Aircraft
-//	Dimensions: 1.484122 x 0.508 m
-//	First Launch: 1965
-//	
-//	Dry Mass: 23.16585 kg
-//	Average Thrust: 25.227 kN
-//	ISP: 284.5 s
-//	Burn Time: 31.5 s
-//	Propellant Mass: 274.4232 kg
 //
+//	=================================================================================
+//	Altair III
+//	FW-4S
+//
+//	Dry Mass: 23.16585 kg
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 25.227 kN
+//	ISP: ??? SL / 284.5 Vac
+//	Burn Time: 31.5
+//	Chamber Pressure: 5.92 MPa
+//	Propellant: CTPB
+//	Prop Ratio: N/A
+//	Throttle: N/A
+//	Nozzle Ratio: ???
+//	Ignitions: 1
+//	=================================================================================
+
+//	Sources:
+
 //	Source: NASA CR-145136 Scout Nozzle Data Book: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19770010201.pdf
 //	Source 1: NASA CR-165950 Scout Launch Vehicle Final Report.PDF)
 //	Source 2: Performance of a UTC FW-4S Solid-Propellant Rocket Motor
 //	  https://apps.dtic.mil/dtic/tr/fulltext/u2/a002149.pdf
-//
-//	===============================================================
 
+//	Used by:
+
+//	Notes:
+
+//	Dimensions: 1.484122 x 0.508 m
+//	Propellant Mass: 274.4232 kg
+//	===============================================================
 @PART[*]:HAS[#engineType[Altair-III]]:FOR[RealismOverhaulEngines]
 {
 	@title = #roAltair-IIITitle	//Altair III FW-4S

GameData/RealismOverhaul/Engine_Configs/Altair_Config.cfg

@@ -1,6 +1,34 @@
-//Altair (X-248)
-//Squad
+//	==================================================
+//	Altair I
 //
+//	Manufacturer: Allegany Ballistics Laboratory
+//
+//	=================================================================================
+//	Altair I
+//	X-248
+//
+//	Dry Mass: 76.74777 kg
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 16.35 kN
+//	ISP: ??? SL / 255.04 Vac
+//	Burn Time: 38.1
+//	Chamber Pressure: 1.49 MPa
+//	Propellant: PBAA
+//	Prop Ratio: N/A
+//	Throttle: N/A
+//	Nozzle Ratio: 25.8
+//	Ignitions: 1
+//	=================================================================================
+
+//	Sources:
+
+//	NASA CR-165950 Scout Launch Vehicle Final Report.PDF
+//	The Vanguard Satellite Launching Vehicle: An Engineering Summary.PDF (1960)
+//	https://i0.wp.com/www.drewexmachina.com/wp-content/uploads/2017/12/ABL_3rd_stage_motor.jpg?ssl=1
+
+//	Used by:
+
+//	Notes:
 //
 // 1974072500-The-Vanguard-Satellite-Launching-Vehicle-an-Engineering-Summary.pdf
 // dimensions p.63 & p.65
@@ -15,27 +43,8 @@
 // 50 + 420 lb	-- 23 + 190 kg	109.1 l
 // 42 + 463 lb	-- 19 + 210 kg	120.65 l
 //
-//	===============================================================
-//
-//	Altair (X-248) SRM
-//	Squad, Bluedog_DB
-//
-//	Manufacturer: Allegany Ballistics Laboratory
-//	Dimensions: 1.47828 x 0.4572 m
-//	First Launch: Vanguard TV-4BU (1959)
-//	
-//	Dry Mass: 22.49816 kg
-//	Average Thrust: 13.34466 kN
-//	ISP: 255.04 s
-//	Burn Time: 39 s
 //	Propellant Mass: 206.2029 kg
-//
-//	Source 1: The Vanguard Satellite Launching Vehicle: An Engineering Summary.PDF (1960)
-//	Source 2: https://i0.wp.com/www.drewexmachina.com/wp-content/uploads/2017/12/ABL_3rd_stage_motor.jpg?ssl=1
-//
 //	===============================================================
-
-
 @PART[*]:HAS[#engineType[Altair]]:FOR[RealismOverhaulEngines]
 {
 	%title = #roAltairTitle	//Altair X-248

GameData/RealismOverhaul/Engine_Configs/Antares_Config.cfg

@@ -12,11 +12,11 @@
 //	Thrust (Vac): 62.27508 kN
 //	ISP: ??? SL / 256 Vac
 //	Burn Time: 38.1
-//	Chamber Pressure: ??? MPa
+//	Chamber Pressure: 2.03 MPa
 //	Propellant: PBAA
 //	Prop Ratio: N/A
 //	Throttle: N/A
-//	Nozzle Ratio: 27
+//	Nozzle Ratio: 25.15
 //	Ignitions: 1
 //	=================================================================================
 

GameData/RealismOverhaul/Engine_Configs/Antares_II_Config.cfg

@@ -12,13 +12,28 @@
 //	Thrust (Vac): 93.074555 kN
 //	ISP: ??? SL / 281.15 Vac
 //	Burn Time: 33.7
-//	Chamber Pressure: ??? MPa
+//	Chamber Pressure: 2.87 MPa
 //	Propellant: PBAA
 //	Prop Ratio: N/A
 //	Throttle: N/A
 //	Nozzle Ratio: 17.5
 //	Ignitions: 1
 //	=================================================================================
+//	Antares IIB
+//	X-259
+//
+//	Dry Mass: 99? kg
+//	Thrust (SL): ??? kN
+//	Thrust (Vac): 126.8 kN
+//	ISP: ??? SL / 284.95 Vac
+//	Burn Time: 28.9
+//	Chamber Pressure: 4.76 MPa
+//	Propellant: PBAA
+//	Prop Ratio: N/A
+//	Throttle: N/A
+//	Nozzle Ratio: ???
+//	Ignitions: 1
+//	=================================================================================
 
 //	Sources: