[Jsbsim-cvslogs] CVS: JSBSim/engine CamelProp.xml, 1.1, 1.2 Clerget9B.xml, 1.1, 1.2

[Erik H. <eh...@us...>]

Update of /cvsroot/jsbsim/JSBSim/engine
In directory sfp-cvs-1.v30.ch3.sourceforge.com:/tmp/cvs-serv30812/engine

Modified Files:
	CamelProp.xml Clerget9B.xml 
Log Message:
Update to the latest version of the Camel config

Index: CamelProp.xml
===================================================================
RCS file: /cvsroot/jsbsim/JSBSim/engine/CamelProp.xml,v
retrieving revision 1.1
retrieving revision 1.2
diff -C2 -r1.1 -r1.2
*** CamelProp.xml	7 Apr 2015 07:52:10 -0000	1.1
--- CamelProp.xml	7 Apr 2015 08:44:58 -0000	1.2
***************
*** 1,206 ****
! <?xml version="1.0"?>

! <!-- Generated by Aero-Matic v 1.1

! 

!      Inputs:

!                 horsepower: 130

!                      pitch: fixed

!             max engine rpm: 1800

!         prop diameter (ft): 9.3305078

! 

!      Outputs:

!               max prop rpm: 2010.93

!                 gear ratio:    0.90

!                        Cp0: 0.011294

!                        Ct0: 0.015811

!        static thrust (lbs):  342.97

!        

!        Sopwith-specific experimental data on a prop/engine is available here, though it is a bit hard to convert between the various units and power & torque

!        measurement systems:

!        http://naca.central.cranfield.ac.uk/reports/arc/rm/448.pdf

! -->

! 

! <propeller name="prop">

!   <!-- <ixx>  22.01 </ixx> --> <!-- Aero-Match generated amount based on 70 lb prop only -->

!   <ixx>  38.01 </ixx> <!-- first WAG based on performance.  Ver 1.6, 5/6/2013, I'm going back to this because it seems to fit descriptions of performance and characteristics best.  I'm not sure if it if the best estimate or if it just fits in best with various other modelling and design decisions. -->

!   <!-- Prop is 18kg per http://books.google.com/books?id=dM8qAAAAMAAJ&pg=PA791&lpg=PA791&dq=sopwith+camel+%22weight+of+wings%22&source=bl&ots=uQJawBEvdL&sig=ectotxNiSI9A0GR-QleJJ3QOYRY&hl=en&ei=eLvCTpiJJZGpsALDqcSLCw&sa=X&oi=book_result&ct=result&resnum=1&ved=0CBoQ6AEwAA#v=onepage&q=sopwith%20camel%20%22weight%20of%20wings%22&f=false 

!   That equals 39.7 pounds and leads to the calculation below.-->

!   <!-- <ixx unit="KG*M2">  20.18 </ixx> --> <!-- See calculation spreadsheet - 12.14 for 18kg prop plus 8.04 for 381 lb clerget (much heavier but also much closer to the center of rotation in than the prop). This is in metric units, kg-m^2.  The rotary engine nearly doubles the moment of inertia compared with inline engine & prop. -->                        

!   

!   <!-- <ixx unit="KG*M2">  12.47 </ixx> --> <!-- "Rough estimate" per historical doc -->

!   

!   <diameter unit="IN"> 112.0 </diameter>

!   <numblades> 2 </numblades>

!   <gearratio>  1.0 </gearratio>        

!   

!   <!-- As generated by Aeromatic: -->

!   <!-- <p_factor>   8.85 </p_factor> -->

!   

!   <!-- The WWI era rotaries were really big engines, over 800 cu. in. so lots of torque. They had a nearly square pitch/diameter ratio that added a lot P-factor too.  http://www.rcgroups.com/forums/archive/index.php/t-789213.html  -->

!  <!--  <p_factor>   19 </p_factor> -->

!   <!-- Setting p_factor=0 was evidently an experiment? -->

!   <!--   <p_factor>   0 </p_factor> -->

!     

!     <!-- As a WAG, let's assume about 1 1/3 X the value calculated by Aeromatic? -->

!     <!-- <p_factor>   11.85 </p_factor> -->

!     <p_factor>   17.85 </p_factor>

!   <!-- <ct_factor> 1</ct_factor> -->

!   <!-- <cp_factor> 1</cp_factor> --> 

! 

!   <!--  -->

!    <!-- best climbing speed of 70mph=60 kt and 16.66 fps climb, 1150 RPM (J=.5358)-->

!    <!-- max speed of 115 kts, level flight, 130 hp, 1250 RPM (J=.976) -->

!    <!-- Additional factor: Starting about 4-5MPH on a grassy runway, 

!    at full throttle the Camel will be airborn in about 6.9 seconds, or

!    approx 7 AC lengths  

!    See: http://www.youtube.com/watch?v=VT9wtDNiKaI  -->

! 

!   <table name="C_THRUST" type="internal">

! <!--     <tableData>

!        

! 		0	   0.092

! 		0.01   0.092

! 		0.1    0.08716

! 		0.2    0.08188

! 		0.3    0.07744

! 		0.4    0.073

! 		0.5    0.0694

! 		0.5358 0.06768

! 		0.64   0.065

! 		0.8    0.06

! 		0.976  0.052013

! 		1.03   0.04536

! 		1.1    0.03312

! 		1.2    0.0144

! 		1.3   -0.0216

! 		1.5   -0.0864

! 		1.7   -0.18

! 		1.9   -0.36

! 		2     -0.72

! 		3     -0.72

! 		5     -0.72

!        

!      </tableData>

!   -->

! <!-- 1.3 trial, this gave perfect match with the 10,000 climb rates chart, but the lift/drag are not giving 48 MPH stall speed, so we need to recalc    <tableData>  

! 0	0.112

! 0.01	0.111

! 0.1	0.11

! 0.2	0.1

! 0.3	0.09

! 0.4	0.08

! 0.5	0.07

! 0.5358	0.06

! 0.64	0.05

! 0.8	0.04

! 0.976	0.03120768

! 1.03	0.027216

! 1.1	0.019872

! 1.2	0.00864

! 1.3	-0.01296

! 1.5	-0.05184

! 1.7	-0.108

! 1.9	-0.216

! 2	-0.432

! 3	-0.432

! 5	-0.432

!     </tableData> -->

! <!-- 1.3, we are trying increased thrust at climb speed to match the10,000 ft climb rate table, with the lift/drag numbers that give 48 MPH stall.  Req more thrust at reduced RPMS 

! 

! See calculations at Camel-JSBSim-calcs-2011-10D.xls, C_THRUST, C_POWER

! 

! -->    

!     <tableData>

!         0	0.097

!         0.1	0.095

!         0.2	0.09

!         0.3	0.08

!         0.4	0.07

!         0.5	0.066

!         0.5657	0.063

!         0.68	0.052

!         0.8	0.044081633

!         0.8611	0.042122449

!         0.976	0.031630189

!         1.04	0.028

!         1.1	0.023

!         1.2	0.013

!         1.3	-0.01

!         1.5	-0.08

!         1.7	-0.19

!         1.9	-0.432

!         2	-0.432

!         3	-2

!         5	-10

!     </tableData>   

!   </table>

! 

! 

!   <table name="C_POWER" type="internal">

!   <!--     

!      <tableData>

!           0      0.06453

!           0.01   0.06453

!           0.1    0.064

!           0.2    0.06353

!           0.3    0.062195

!           0.4    0.060133

!           0.5    0.058

!           0.5358 0.056814

!           0.64   0.055

!           0.8    0.05184

!           0.976  0.049032

!           1.03   0.047816

!           1.1    0.04286

!           1.2    0.036

!           1.3    0.0216

!           1.5   -0.0072

!           1.7   -0.036

!           1.9   -0.0864

!           2     -0.0864

!           3     -0.1152

!           5     -0.288

!      </tableData>

!      -->

!      <tableData>

!         0	0.0561411

!         0.01	0.0561411

!         0.1	0.05568

!         0.2	0.0552711

!         0.3	0.054109824

!         0.4	0.052315884

!         0.5	0.05046

!         0.5358	0.04942818

!         0.64	0.04785

!         0.8	0.0451008

!         0.976	0.04265784

!         1.03	0.04159992

!         1.1	0.0372882

!         1.2	0.03132

!         1.3	0.018792

!         1.5	-0.006264

!         1.7	-0.03132

!         1.9	-0.075168

!         2	-0.075168

!         3	-0.100224

!         5	-0.25056

!      </tableData>

!   </table>

! 

!   <!-- thrust effects of helical tip Mach -->

!   <table name="CT_MACH" type="internal">

!     <tableData>

!       0.85   1.0

!       1.05   0.8

!     </tableData>

!   </table>

!   

!   <!-- power-required effects of helical tip Mach -->

!   <table name="CP_MACH" type="internal">

!     <tableData>

!       0.85   1.0

!       1.05   1.8

!       2.00   1.4

!     </tableData>

!   </table>

! 

  </propeller>
\ No newline at end of file
--- 1,206 ----
! <?xml version="1.0"?>
! <!-- Generated by Aero-Matic v 1.1
! 
!      Inputs:
!                 horsepower: 130
!                      pitch: fixed
!             max engine rpm: 1800
!         prop diameter (ft): 9.3305078
! 
!      Outputs:
!               max prop rpm: 2010.93
!                 gear ratio:    0.90
!                        Cp0: 0.011294
!                        Ct0: 0.015811
!        static thrust (lbs):  342.97
!        
!        Sopwith-specific experimental data on a prop/engine is available here, though it is a bit hard to convert between the various units and power & torque
!        measurement systems:
!        http://naca.central.cranfield.ac.uk/reports/arc/rm/448.pdf
! -->
! 
! <propeller name="prop">
!   <!-- <ixx>  22.01 </ixx> --> <!-- Aero-Match generated amount based on 70 lb prop only -->
!   <ixx>  38.01 </ixx> <!-- first WAG based on performance.  Ver 1.6, 5/6/2013, I'm going back to this because it seems to fit descriptions of performance and characteristics best.  I'm not sure if it if the best estimate or if it just fits in best with various other modelling and design decisions. -->
!   <!-- Prop is 18kg per http://books.google.com/books?id=dM8qAAAAMAAJ&pg=PA791&lpg=PA791&dq=sopwith+camel+%22weight+of+wings%22&source=bl&ots=uQJawBEvdL&sig=ectotxNiSI9A0GR-QleJJ3QOYRY&hl=en&ei=eLvCTpiJJZGpsALDqcSLCw&sa=X&oi=book_result&ct=result&resnum=1&ved=0CBoQ6AEwAA#v=onepage&q=sopwith%20camel%20%22weight%20of%20wings%22&f=false 
!   That equals 39.7 pounds and leads to the calculation below.-->
!   <!-- <ixx unit="KG*M2">  20.18 </ixx> --> <!-- See calculation spreadsheet - 12.14 for 18kg prop plus 8.04 for 381 lb clerget (much heavier but also much closer to the center of rotation in than the prop). This is in metric units, kg-m^2.  The rotary engine nearly doubles the moment of inertia compared with inline engine & prop. -->                        
!   
!   <!-- <ixx unit="KG*M2">  12.47 </ixx> --> <!-- "Rough estimate" per historical doc -->
!   
!   <diameter unit="IN"> 112.0 </diameter>
!   <numblades> 2 </numblades>
!   <gearratio>  1.0 </gearratio>        
!   
!   <!-- As generated by Aeromatic: -->
!   <!-- <p_factor>   8.85 </p_factor> -->
!   
!   <!-- The WWI era rotaries were really big engines, over 800 cu. in. so lots of torque. They had a nearly square pitch/diameter ratio that added a lot P-factor too.  http://www.rcgroups.com/forums/archive/index.php/t-789213.html  -->
!  <!--  <p_factor>   19 </p_factor> -->
!   <!-- Setting p_factor=0 was evidently an experiment? -->
!   <!--   <p_factor>   0 </p_factor> -->
!     
!     <!-- As a WAG, let's assume about 1 1/3 X the value calculated by Aeromatic? -->
!     <!-- <p_factor>   11.85 </p_factor> -->
!     <p_factor>   17.85 </p_factor>
!   <!-- <ct_factor> 1</ct_factor> -->
!   <!-- <cp_factor> 1</cp_factor> --> 
! 
!   <!--  -->
!    <!-- best climbing speed of 70mph=60 kt and 16.66 fps climb, 1150 RPM (J=.5358)-->
!    <!-- max speed of 115 kts, level flight, 130 hp, 1250 RPM (J=.976) -->
!    <!-- Additional factor: Starting about 4-5MPH on a grassy runway, 
!    at full throttle the Camel will be airborn in about 6.9 seconds, or
!    approx 7 AC lengths  
!    See: http://www.youtube.com/watch?v=VT9wtDNiKaI  -->
! 
!   <table name="C_THRUST" type="internal">
! <!--     <tableData>
!        
! 		0	   0.092
! 		0.01   0.092
! 		0.1    0.08716
! 		0.2    0.08188
! 		0.3    0.07744
! 		0.4    0.073
! 		0.5    0.0694
! 		0.5358 0.06768
! 		0.64   0.065
! 		0.8    0.06
! 		0.976  0.052013
! 		1.03   0.04536
! 		1.1    0.03312
! 		1.2    0.0144
! 		1.3   -0.0216
! 		1.5   -0.0864
! 		1.7   -0.18
! 		1.9   -0.36
! 		2     -0.72
! 		3     -0.72
! 		5     -0.72
!        
!      </tableData>
!   -->
! <!-- 1.3 trial, this gave perfect match with the 10,000 climb rates chart, but the lift/drag are not giving 48 MPH stall speed, so we need to recalc    <tableData>  
! 0	0.112
! 0.01	0.111
! 0.1	0.11
! 0.2	0.1
! 0.3	0.09
! 0.4	0.08
! 0.5	0.07
! 0.5358	0.06
! 0.64	0.05
! 0.8	0.04
! 0.976	0.03120768
! 1.03	0.027216
! 1.1	0.019872
! 1.2	0.00864
! 1.3	-0.01296
! 1.5	-0.05184
! 1.7	-0.108
! 1.9	-0.216
! 2	-0.432
! 3	-0.432
! 5	-0.432
!     </tableData> -->
! <!-- 1.3, we are trying increased thrust at climb speed to match the10,000 ft climb rate table, with the lift/drag numbers that give 48 MPH stall.  Req more thrust at reduced RPMS 
! 
! See calculations at Camel-JSBSim-calcs-2011-10D.xls, C_THRUST, C_POWER
! 
! -->    
!     <tableData>
!         0	0.097
!         0.1	0.095
!         0.2	0.09
!         0.3	0.08
!         0.4	0.07
!         0.5	0.066
!         0.5657	0.063
!         0.68	0.052
!         0.8	0.044081633
!         0.8611	0.042122449
!         0.976	0.031630189
!         1.04	0.028
!         1.1	0.023
!         1.2	0.013
!         1.3	-0.01
!         1.5	-0.08
!         1.7	-0.19
!         1.9	-0.432
!         2	-0.432
!         3	-2
!         5	-10
!     </tableData>   
!   </table>
! 
! 
!   <table name="C_POWER" type="internal">
!   <!--     
!      <tableData>
!           0      0.06453
!           0.01   0.06453
!           0.1    0.064
!           0.2    0.06353
!           0.3    0.062195
!           0.4    0.060133
!           0.5    0.058
!           0.5358 0.056814
!           0.64   0.055
!           0.8    0.05184
!           0.976  0.049032
!           1.03   0.047816
!           1.1    0.04286
!           1.2    0.036
!           1.3    0.0216
!           1.5   -0.0072
!           1.7   -0.036
!           1.9   -0.0864
!           2     -0.0864
!           3     -0.1152
!           5     -0.288
!      </tableData>
!      -->
!      <tableData>
!         0	0.0561411
!         0.01	0.0561411
!         0.1	0.05568
!         0.2	0.0552711
!         0.3	0.054109824
!         0.4	0.052315884
!         0.5	0.05046
!         0.5358	0.04942818
!         0.64	0.04785
!         0.8	0.0451008
!         0.976	0.04265784
!         1.03	0.04159992
!         1.1	0.0372882
!         1.2	0.03132
!         1.3	0.018792
!         1.5	-0.006264
!         1.7	-0.03132
!         1.9	-0.075168
!         2	-0.075168
!         3	-0.100224
!         5	-0.25056
!      </tableData>
!   </table>
! 
!   <!-- thrust effects of helical tip Mach -->
!   <table name="CT_MACH" type="internal">
!     <tableData>
!       0.85   1.0
!       1.05   0.8
!     </tableData>
!   </table>
!   
!   <!-- power-required effects of helical tip Mach -->
!   <table name="CP_MACH" type="internal">
!     <tableData>
!       0.85   1.0
!       1.05   1.8
!       2.00   1.4
!     </tableData>
!   </table>
! 
  </propeller>
\ No newline at end of file

Index: Clerget9B.xml
===================================================================
RCS file: /cvsroot/jsbsim/JSBSim/engine/Clerget9B.xml,v
retrieving revision 1.1
retrieving revision 1.2
diff -C2 -r1.1 -r1.2
*** Clerget9B.xml	7 Apr 2015 07:52:10 -0000	1.1
--- Clerget9B.xml	7 Apr 2015 08:44:58 -0000	1.2
***************
*** 1,78 ****
! <?xml version="1.0"?>

! <!--

!   File:     Clerget9B.xml

!   Author:   Aero-Matic v 0.82

! 

!   Inputs:

!     name:           Clerget9B

!     type:           piston

!     power:          130 hp

!     augmented?      no

!     injected?       no

!     

!     the clerget 130hp 9b is as follows:

! 

! no. of cylinders...........................9

! bore..........................................120 mm

! stroke........................................160 mm

! weight complete...........................381 lbs

! compression ratio..........................4:1

! normal h.p....................................130

! effective h.p.................................135

! r.p.m...........................................12 50

! oil consumption per h.p. hour............   0.09 pints

! petrol consumption per h.p. hour.......   0.74 pints

! [0.74 pints = 0.0925 gallons; 6.073 pounds per gallon of gasoline =   .5617525 pounds per hp hr.       In grams per kW hr that is  341.701125 ]

! 

! the 110 hp 9z is:

! 

! no. of cylinders..............................9

! bore.............................................1 20 mm

! stroke..........................................16 0 mm

! weight complete.............................397 lbs

! compression ratio............................4:1

! normal h.p.....................................110

! effective h.p..................................115

! r.p.m............................................. 1180

! oil consumption per h.p. hour............ 0.14 pints

! petrol consumption per h.p. hour........ 0.75 pints

! 

! the 140 hp 9bf *is:

! 

! no. of cylinders ................................9

! bore.............................................. .120 mm

! stroke............................................ .172 mm

! weight complete...............................381 lbs

! compression ratio..............................5.3:1

! normal h.p.......................................140

! effective h.p....................................153

! r.p.m............................................. .1250

! oil consumption per h.p. hour.............. 0.11 pints

! petrol consumption per h.p. hour......... 0.59 pints

! 

! SRC: http://www.theaerodrome.com/forum/2001/10278-clerget-9b-fuel-consumption.html

! -->

! 

! <piston_engine name="Clerget9B">

!   <minmp unit="INHG">          23.0 </minmp>

!   <maxmp unit="INHG">         28.5 </maxmp>

!   <displacement unit="IN3"> 993.8 </displacement>

!   <maxhp unit="HP">        130.00 </maxhp>

!   <cycles>         4.0 </cycles>

!   <idlerpm>      300.0 </idlerpm>

!   <maxrpm>      1250.0 </maxrpm>

!   <maxthrottle>    1.0 </maxthrottle><!-- Deprecated -->

!   <minthrottle>    0.1 </minthrottle><!-- Deprecated -->

!   <sparkfaildrop>  0.17 </sparkfaildrop>

!   

!   <volumetric-efficiency> 0.673 </volumetric-efficiency>

! <!-- Optional items that affect engine performance -->

!  <!-- Defining <bsfc> over-rides the built-in horsepower calculations -->

! <bsfc unit="LBS/HP*HR"> 0.54 </bsfc> <!-- 0.5617525 is the calculated amount but the JSBSim manual says that JSBSim incorporates some of this internally so the number may need to be reduced some.  0.353 gives the rated top speed of 116 kts for the Camel at high rpm with unaltered CamelProp.xml.  But with the adjusted CamelProp C_THRUST values it is more like .50-->

!  <stroke unit="IN">  6.2992  </stroke>

!  <bore unit="IN">    4.72441 </bore>

!  <cylinders>         9.0  </cylinders>

!  <compression-ratio> 4.0 </compression-ratio> 

!  

!  

  </piston_engine>
\ No newline at end of file
--- 1,78 ----
! <?xml version="1.0"?>
! <!--
!   File:     Clerget9B.xml
!   Author:   Aero-Matic v 0.82
! 
!   Inputs:
!     name:           Clerget9B
!     type:           piston
!     power:          130 hp
!     augmented?      no
!     injected?       no
!     
!     the clerget 130hp 9b is as follows:
! 
! no. of cylinders...........................9
! bore..........................................120 mm
! stroke........................................160 mm
! weight complete...........................381 lbs
! compression ratio..........................4:1
! normal h.p....................................130
! effective h.p.................................135
! r.p.m...........................................12 50
! oil consumption per h.p. hour............   0.09 pints
! petrol consumption per h.p. hour.......   0.74 pints
! [0.74 pints = 0.0925 gallons; 6.073 pounds per gallon of gasoline =   .5617525 pounds per hp hr.       In grams per kW hr that is  341.701125 ]
! 
! the 110 hp 9z is:
! 
! no. of cylinders..............................9
! bore.............................................1 20 mm
! stroke..........................................16 0 mm
! weight complete.............................397 lbs
! compression ratio............................4:1
! normal h.p.....................................110
! effective h.p..................................115
! r.p.m............................................. 1180
! oil consumption per h.p. hour............ 0.14 pints
! petrol consumption per h.p. hour........ 0.75 pints
! 
! the 140 hp 9bf *is:
! 
! no. of cylinders ................................9
! bore.............................................. .120 mm
! stroke............................................ .172 mm
! weight complete...............................381 lbs
! compression ratio..............................5.3:1
! normal h.p.......................................140
! effective h.p....................................153
! r.p.m............................................. .1250
! oil consumption per h.p. hour.............. 0.11 pints
! petrol consumption per h.p. hour......... 0.59 pints
! 
! SRC: http://www.theaerodrome.com/forum/2001/10278-clerget-9b-fuel-consumption.html
! -->
! 
! <piston_engine name="Clerget9B">
!   <minmp unit="INHG">          23.0 </minmp>
!   <maxmp unit="INHG">         28.5 </maxmp>
!   <displacement unit="IN3"> 993.8 </displacement>
!   <maxhp unit="HP">        130.00 </maxhp>
!   <cycles>         4.0 </cycles>
!   <idlerpm>      300.0 </idlerpm>
!   <maxrpm>      1250.0 </maxrpm>
!   <maxthrottle>    1.0 </maxthrottle><!-- Deprecated -->
!   <minthrottle>    0.1 </minthrottle><!-- Deprecated -->
!   <sparkfaildrop>  0.17 </sparkfaildrop>
!   
!   <volumetric-efficiency> 0.673 </volumetric-efficiency>
! <!-- Optional items that affect engine performance -->
!  <!-- Defining <bsfc> over-rides the built-in horsepower calculations -->
! <bsfc unit="LBS/HP*HR"> 0.54 </bsfc> <!-- 0.5617525 is the calculated amount but the JSBSim manual says that JSBSim incorporates some of this internally so the number may need to be reduced some.  0.353 gives the rated top speed of 116 kts for the Camel at high rpm with unaltered CamelProp.xml.  But with the adjusted CamelProp C_THRUST values it is more like .50-->
!  <stroke unit="IN">  6.2992  </stroke>
!  <bore unit="IN">    4.72441 </bore>
!  <cylinders>         9.0  </cylinders>
!  <compression-ratio> 4.0 </compression-ratio> 
!  
!  
  </piston_engine>
\ No newline at end of file