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Updated thrustcurves.

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This commit is contained in:
kruland2607 2013-09-03 14:41:34 -05:00
parent 11c5e072f0
commit 54871ec674
21 changed files with 564 additions and 164 deletions
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72
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_G80.eng
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@ -1,37 +1,37 @@
; 136 N-sec G80, Certified Nov. 2007. As published by NAR S&T.
;G80 New Blue Thunder
G80NBT 29 123.825 4-7-10 0.069 0.129 AT
0.013 89.054
0.018 101.584
0.029 105.388
0.047 102.927
0.104 100.018
0.19 102.255
0.268 104.94
0.306 104.269
0.352 105.835
0.41 104.94
0.432 106.73
0.512 105.612
0.563 106.954
0.591 104.493
0.62 106.283
0.715 103.15
0.76 103.374
0.806 101.36
0.848 102.032
1.2 88.383
1.243 77.866
1.269 57.952
1.302 44.079
1.329 34.011
1.367 26.403
1.398 22.823
1.433 20.585
1.48 21.704
1.508 20.809
1.584 13.201
1.604 11.635
1.652 11.188
1.683 5.37
1.701 0
;
; @File: NewATG80.txt, @Pts-I: 905, @Pts-O: 31, @Sm: 0, @CO: 5%
; @TI: 133.2377, @TIa: 133.1309, @TIe: 0.0%, @ThMax: 102.2, @ThAvg: 77.9911, @Tb: 1.707
; Exported using ThrustCurveTool, www.ThrustGear.com
G78 29 128 7,10,13 0.0625 0.1282 RCS/Aerotech
0.0060 1.158086
0.0080 7.48984
0.01 33.7575
0.012 64.5955
0.014 62.9316
0.016 58.8272
0.018 74.9118
0.02 85.0062
0.022 91.1072
0.026 93.9913
0.028 98.4284
0.032 97.652
0.038 102.2
0.074 97.3192
0.124 95.4334
0.376 99.3159
0.68 99.4268
0.994 91.6619
1.2459 83.0095
1.2819 77.3522
1.3159 61.9332
1.3599 44.6285
1.4239 29.0986
1.5039 21.2227
1.5979 19.33693
1.6559 16.34188
1.6759 13.90147
1.6779 11.79384
1.7139 5.0938
1.7339 1.388816
1.8079 0.0

65
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_G80_1.eng
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@ -1,28 +1,37 @@
; AEROTECH G80 RASP.ENG FILE
; Note: this is for the 94 N-sec G80T certified in Sept. 2006
G80 29 124 4-7-10 0.0479 0.1129998 AERO
0.0060 84.371
0.018 118.23
0.027 109.378
0.037 101.35
0.042 105.565
0.059 98.37
0.113 95.821
0.185 96.252
0.277 94.556
0.404 94.978
0.526 91.165
0.671 87.1
0.792 82.675
0.885 77.166
0.943 73.353
0.971 68.266
0.997 57.237
1.03 48.337
1.059 40.279
1.085 27.986
1.112 17.811
1.144 10.175
1.168 5.512
1.182 2.968
1.21 0.0
; 136 N-sec G80, Certified Nov. 2007. As published by NAR S&T.
;
; @File: NewATG80.txt, @Pts-I: 905, @Pts-O: 31, @Sm: 0, @CO: 5%
; @TI: 133.2377, @TIa: 133.1309, @TIe: 0.0%, @ThMax: 102.2, @ThAvg: 77.9911, @Tb: 1.707
; Exported using ThrustCurveTool, www.ThrustGear.com
G78 29 128 7,10,13 0.0625 0.1282 RCS/Aerotech
0.0060 1.158086
0.0080 7.48984
0.01 33.7575
0.012 64.5955
0.014 62.9316
0.016 58.8272
0.018 74.9118
0.02 85.0062
0.022 91.1072
0.026 93.9913
0.028 98.4284
0.032 97.652
0.038 102.2
0.074 97.3192
0.124 95.4334
0.376 99.3159
0.68 99.4268
0.994 91.6619
1.2459 83.0095
1.2819 77.3522
1.3159 61.9332
1.3599 44.6285
1.4239 29.0986
1.5039 21.2227
1.5979 19.33693
1.6559 16.34188
1.6759 13.90147
1.6779 11.79384
1.7139 5.0938
1.7339 1.388816
1.8079 0.0

62
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_G80_2.eng
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@ -1,34 +1,28 @@
; Aerotech G80 RASP.ENG file made from NAR published data
; File produced July 4, 2000
; Note: This is for the 116N-sec G80T produced before Sept. 2006
G80 29 124 4-7-10 0.0574 0.1049 A
0.0060 101.291
0.013 105.18
0.031 103.473
0.038 104.069
0.067 99.803
0.103 96.906
0.181 94.733
0.271 94.039
0.303 96.985
0.367 95.547
0.428 94.842
0.456 97.055
0.463 92.65
0.51 94.872
0.596 93.444
0.606 95.646
0.624 91.985
0.635 95.656
0.646 91.995
0.696 90.547
0.846 85.477
0.96 80.388
1.071 74.564
1.207 62.878
1.296 52.639
1.35 37.252
1.382 20.397
1.418 10.139
1.457 4.281
1.5 0.0
; AEROTECH G80 RASP.ENG FILE
; Note: this is for the 94 N-sec G80T certified in Sept. 2006
G80 29 124 4-7-10 0.0479 0.1129998 AERO
0.0060 84.371
0.018 118.23
0.027 109.378
0.037 101.35
0.042 105.565
0.059 98.37
0.113 95.821
0.185 96.252
0.277 94.556
0.404 94.978
0.526 91.165
0.671 87.1
0.792 82.675
0.885 77.166
0.943 73.353
0.971 68.266
0.997 57.237
1.03 48.337
1.059 40.279
1.085 27.986
1.112 17.811
1.144 10.175
1.168 5.512
1.182 2.968
1.21 0.0

34
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_G80_3.eng Normal file
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; Aerotech G80 RASP.ENG file made from NAR published data
; File produced July 4, 2000
; Note: This is for the 116N-sec G80T produced before Sept. 2006
G80 29 124 4-7-10 0.0574 0.1049 A
0.0060 101.291
0.013 105.18
0.031 103.473
0.038 104.069
0.067 99.803
0.103 96.906
0.181 94.733
0.271 94.039
0.303 96.985
0.367 95.547
0.428 94.842
0.456 97.055
0.463 92.65
0.51 94.872
0.596 93.444
0.606 95.646
0.624 91.985
0.635 95.656
0.646 91.995
0.696 90.547
0.846 85.477
0.96 80.388
1.071 74.564
1.207 62.878
1.296 52.639
1.35 37.252
1.382 20.397
1.418 10.139
1.457 4.281
1.5 0.0

24
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_H195.eng Normal file
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H195NBT 29 203.2 10 0.115 0.197 AT
0.003 178.052
0.005 224.131
0.013 252.516
0.019 256.571
0.022 248.461
0.058 239.614
0.1 240.351
0.199 235.559
0.255 228.555
0.285 227.449
0.301 230.767
0.399 223.025
0.5 223.025
0.603 220.445
0.774 217.127
0.802 211.598
0.899 201.644
0.961 180.632
0.999 169.942
1.023 161.094
1.054 155.196
1.101 69.304
1.169 0.0

25
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_I140.eng Normal file
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; AT I140W DMS
I140W 38 202.7 14-12-10-8-6 0.183 0.356 AT
0.011 96.257
0.024 80.214
0.049 160.428
0.062 144.02
0.114 160.428
0.159 164.074
0.238 174.647
0.314 173.918
0.419 179.023
0.627 178.293
0.835 176.835
0.943 177.2
1.146 164.803
1.349 148.76
1.459 141.103
1.562 131.259
1.773 113.393
2.192 83.86
2.295 67.088
2.395 37.555
2.435 31.356
2.47 20.418
2.478 0.0

34
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_I280.eng Normal file
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@ -0,0 +1,34 @@
; I280DM DMS
I280DM 38 356.4 14-12-10-8-6 0.355 0.616 AT
0.016 342.389
0.048 297.021
0.111 316.16
0.173 328.211
0.202 327.502
0.261 322.54
0.334 311.907
0.498 310.489
0.602 308.363
0.705 307.654
0.802 310.489
0.902 310.489
1.0 306.236
1.025 316.869
1.057 309.072
1.1 308.363
1.139 317.578
1.205 307.654
1.298 304.109
1.336 316.16
1.4 299.856
1.5 296.312
1.55 298.438
1.595 306.945
1.634 295.603
1.652 280.716
1.716 253.07
1.743 224.006
1.8 153.827
1.9 62.381
1.97 20.558
1.971 0.0

40
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_J270.eng Normal file
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@ -0,0 +1,40 @@
; J270W DMS
J270W 38 356.4 14-12-10-8-6 0.381 0.642 AT
0.007 367.585
0.02 325.124
0.074 353.027
0.136 329.977
0.176 343.928
0.273 324.518
0.33 342.715
0.357 326.338
0.399 330.584
0.473 310.567
0.553 325.731
0.734 340.895
0.744 357.273
0.761 315.419
0.788 337.256
0.897 340.895
1.009 333.617
1.053 354.24
1.105 320.878
1.18 345.748
1.214 321.485
1.249 345.748
1.274 314.206
1.5 316.026
1.601 309.96
1.916 303.894
1.956 265.073
2.0 214.121
2.052 179.546
2.102 158.923
2.201 117.676
2.268 106.151
2.303 87.953
2.369 55.805
2.407 49.739
2.486 39.427
2.558 21.837
2.563 0.0

79
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_M1780.eng
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@ -1,42 +1,37 @@
; AT M1780NT 1" Core Revised
M1780NT 75 665 P 2.371 4.606 AT
0.0090 1337.154
0.026 2005.731
0.04 2106.521
0.046 2163.636
0.085 2156.916
0.108 2126.679
0.134 2113.24
0.168 2130.039
0.205 2126.679
0.259 2197.233
0.299 2156.916
0.347 2130.039
0.399 2123.32
0.495 2103.161
0.595 2089.723
0.697 2079.644
0.8 2083.003
0.9 2076.284
0.999 2069.565
1.201 2056.126
1.398 2029.248
1.603 2002.371
1.799 1965.414
1.998 1904.94
2.2 1817.588
2.3 1757.114
2.354 1723.517
2.405 1713.438
2.46 1629.446
2.502 1558.893
2.571 1333.794
2.622 1115.415
2.67 890.316
2.724 665.217
2.758 571.146
2.798 507.312
2.83 446.838
2.901 265.415
3.003 73.913
3.035 0.0
; M1780NT Redesign and recert
M1780NT-PS 75 665 P 2.46 4.649 AT
0.014 1112.055
0.015 1497.932
0.022 1783.542
0.036 2105.612
0.047 2157.265
0.066 2169.419
0.104 2123.843
0.14 2108.651
0.164 2135.996
0.197 2129.92
0.238 2157.265
0.263 2205.88
0.274 2169.419
0.312 2145.112
0.411 2111.689
0.595 2081.305
0.899 2075.228
1.299 2047.883
1.601 1996.23
1.899 1938.5
2.058 1889.886
2.201 1813.926
2.3 1753.158
2.423 1701.505
2.467 1622.506
2.508 1555.662
2.566 1336.897
2.62 1112.055
2.67 893.29
2.724 668.448
2.755 568.181
2.812 486.144
2.9 267.379
2.999 75.96
3.029 0.0

65
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_M1780_1.eng
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@ -1,23 +1,42 @@
M1780 75 665 P 2.56 4.715 AT
0.028 2204.193
0.118 2566.025
0.173 2566.025
0.341 2214.151
0.44 2144.44
0.636 2114.564
1.34 2134.482
1.395 2204.193
1.648 2121.203
1.841 2041.534
1.874 1895.473
2.127 1643.186
2.353 1517.042
2.584 1460.61
2.672 1347.744
2.763 1068.901
2.829 723.666
2.939 438.183
2.999 292.122
3.101 172.617
3.272 36.515
3.5 0.0
; AT M1780NT 1" Core Revised
M1780NT 75 665 P 2.371 4.606 AT
0.0090 1337.154
0.026 2005.731
0.04 2106.521
0.046 2163.636
0.085 2156.916
0.108 2126.679
0.134 2113.24
0.168 2130.039
0.205 2126.679
0.259 2197.233
0.299 2156.916
0.347 2130.039
0.399 2123.32
0.495 2103.161
0.595 2089.723
0.697 2079.644
0.8 2083.003
0.9 2076.284
0.999 2069.565
1.201 2056.126
1.398 2029.248
1.603 2002.371
1.799 1965.414
1.998 1904.94
2.2 1817.588
2.3 1757.114
2.354 1723.517
2.405 1713.438
2.46 1629.446
2.502 1558.893
2.571 1333.794
2.622 1115.415
2.67 890.316
2.724 665.217
2.758 571.146
2.798 507.312
2.83 446.838
2.901 265.415
3.003 73.913
3.035 0.0

2
core/resources-src/datafiles/thrustcurves/thrustcurve.org/AeroTech_M685.eng
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@ -1,5 +1,5 @@
; M685W-PS Moonburner
M685W-PS 75 801 P 4.32 7.008 AT
M685W-PS 75 936 P 4.32 7.008 AT
0.083 1333.469
0.13 1368.376
0.249 1361.395

15
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_G145.eng Normal file
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@ -0,0 +1,15 @@
;
; Pro24-6G 140G145-PK Pink
;based on RockSim file by Mark Koelsch
G145-PK 24 228 0 0.0772 0.1619 CTI
0.007 286.726
0.013 346.018
0.022 310.619
0.039 226.991
0.066 206.097
0.343 174.779
0.672 138.496
0.775 75.664
0.899 29.204
0.982 13.274
1.015 0

14
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_M1830.eng Normal file
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@ -0,0 +1,14 @@
;
; Pro75-4G 5604M1830-CS C-Star
;based on RockSim file by Mark Koelsch
M1830-CS 75 621 0 2.666 4.524 CTI
0.018 2300.79
0.028 1952.86
0.155 2008.98
1.111 2121.21
1.452 2053.87
1.782 1958.47
2.608 1694.72
2.677 1546.02
3.06 115.039
3.165 0

16
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_N2200.eng Normal file
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@ -0,0 +1,16 @@
;
; Pro98-5G 12066N2200-PK Pink
;based on RockSim file by Mark Koelsch
N2200-PK 98 1010 0 6.308 11.356 CTI
0.033 2755.85
0.143 2434.78
0.624 2555.18
1.814 2602.01
2.67 2461.54
4.186 2130.43
4.66 2063.55
4.796 1852.84
5.067 775.92
5.236 474.916
5.497 180.602
5.86 0

30
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_N2900.rse Normal file
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@ -0,0 +1,30 @@
<engine-database>
<engine-list>
<engine mfg="CTI" code="N2900-CL" Type="unspecified" dia="98." len="1239."
initWt="14166." propWt="8788." delays="0" auto-calc-mass="1" auto-calc-cg="1"
avgThrust="2818.38" peakThrust="4022.13" throatDia="0." exitDia="0."
Itot="17744.5" burn-time="6.3" massFrac="62.04" Isp="205.9" tDiv="10" tStep="-1."
tFix="1" FDiv="10" FStep="-1." FFix="1" mDiv="10" mStep="-1." mFix="1" cgDiv="10"
cgStep="-1." cgFix="1">
<comments>Pro98-6GXL 17613N2900-CL P</comments>
<data>
<eng-data t="0." f="0." m="8788." cg="619.5"/>
<eng-data t="0.026" f="1863.57" m="8776." cg="619.5"/>
<eng-data t="0.074" f="3605.4" m="8711." cg="619.5"/>
<eng-data t="0.122" f="4022.13" m="8620.34" cg="619.5"/>
<eng-data t="0.361" f="3619.45" m="8168.09" cg="619.5"/>
<eng-data t="1.18" f="3497.71" m="6724.69" cg="619.5"/>
<eng-data t="1.981" f="3586.67" m="5319.51" cg="619.5"/>
<eng-data t="3.493" f="3155.89" m="2795.02" cg="619.5"/>
<eng-data t="4.648" f="2874.95" m="1070.15" cg="619.5"/>
<eng-data t="4.939" f="2322.44" m="695.633" cg="619.5"/>
<eng-data t="5.205" f="1648.18" m="434.094" cg="619.5"/>
<eng-data t="5.629" f="945.832" m="161.739" cg="619.5"/>
<eng-data t="5.972" f="430.775" m="44.8158" cg="619.5"/>
<eng-data t="6.219" f="206.023" m="5.86692" cg="619.5"/>
<eng-data t="6.278" f="149.835" m="0.667855" cg="619.5"/>
<eng-data t="6.296" f="0." m="0." cg="619.5"/>
</data>
</engine>
</engine-list>
</engine-database>

23
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_N5600.eng Normal file
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@ -0,0 +1,23 @@
N5600WT 98 1010 P 6.363 11.28 CTI
0.019 6750.0
0.041 6250.0
0.044 6078.947
0.077 5960.526
0.198 6144.737
0.749 6328.947
0.931 6447.368
1.049 6368.421
1.25 6118.421
1.501 5828.947
1.751 5500.0
1.999 5263.158
2.131 5131.579
2.17 5144.737
2.2 4986.842
2.252 4013.158
2.291 3013.158
2.335 2000.0
2.373 1000.0
2.401 500.0
2.448 171.053
2.483 0.0

27
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Cesaroni_N5600.rse Normal file
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@ -0,0 +1,27 @@
<engine-database>
<engine-list>
<engine mfg="CTI" code="13628-N5600-WT-P" Type="unspecified" dia="98." len="1010."
initWt="11280." propWt="6486." delays="0" auto-calc-mass="1" auto-calc-cg="1"
avgThrust="5538.49" peakThrust="6592.69" throatDia="0." exitDia="0."
Itot="13635.8" burn-time="2.46" massFrac="57.5" Isp="214.38" tDiv="10"
tStep="-1." tFix="1" FDiv="10" FStep="-1." FFix="1" mDiv="10" mStep="-1."
mFix="1" cgDiv="10" cgStep="-1." cgFix="1">
<comments>CTI Pro-98 6G
13628 N5600-WT P
</comments>
<data>
<eng-data t="0." f="0." m="6486." cg="505."/>
<eng-data t="0.024" f="6592.69" m="6448.37" cg="505."/>
<eng-data t="0.064" f="5986.47" m="6328.7" cg="505."/>
<eng-data t="0.309" f="6213.8" m="5617.81" cg="505."/>
<eng-data t="0.806" f="6376.18" m="4129.65" cg="505."/>
<eng-data t="0.921" f="6451.96" m="3778.8" cg="505."/>
<eng-data t="2.14" f="5131.26" m="420.646" cg="505."/>
<eng-data t="2.186" f="5109.61" m="308.609" cg="505."/>
<eng-data t="2.215" f="4849.8" m="239.918" cg="505."/>
<eng-data t="2.38" f="844.384" m="16.4672" cg="505."/>
<eng-data t="2.462" f="0." m="0." cg="505."/>
</data>
</engine>
</engine-list>
</engine-database>

36
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Estes_E16.eng Normal file
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@ -0,0 +1,36 @@
; File produced, 2013
; The total impulse, peak thrust, average thrust and burn time are
; the same as the averaged static test data on the NAR web site in
; the certification file. The curve drawn with these data points is as
; close to the certification curve as can be with such a limited
; number of points (32) allowed with wRASP up to v1.6.
E16 29 114 0-4-6-8 .0400 .08200 E
0.150 1.371
0.186 1.920
0.206 3.387
0.242 5.587
0.252 7.422
0.277 8.705
0.333 13.474
0.359 15.858
0.374 16.592
0.394 18.609
0.435 21.544
0.476 24.661
0.521 26.440
0.643 21.720
0.725 20.432
0.821 19.511
0.898 18.958
1.025 18.219
1.142 18.032
1.259 17.844
1.396 17.472
1.569 17.282
1.757 17.275
1.895 17.086
2.027 17.816
2.042 12.494
2.052 8.457
2.063 4.970
2.090 0.000

34
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Estes_F15.eng Normal file
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; Estes F15 RASP.ENG file made from NAR published data
; File produced, 2013
; The total impulse, peak thrust, average thrust and burn time are
; the same as the averaged static test data on the NAR web site in
; the certification file. The curve drawn with these data points is as
; close to the certification curve as can be with such a limited
; number of points (32) allowed with wRASP up to v1.6.
F15 29 114 0-4-6-8 .0600 .10300 E
0.148 7.638
0.228 12.253
0.294 16.391
0.353 20.210
0.382 22.756
0.419 25.260
0.477 23.074
0.520 20.845
0.593 19.093
0.688 17.500
0.855 16.225
1.037 15.427
1.205 14.948
1.423 14.627
1.452 15.741
1.503 14.785
1.736 14.623
1.955 14.303
2.210 14.141
2.494 13.819
2.763 13.338
3.120 13.334
3.382 13.013
3.404 9.352
3.418 4.895
3.450 0.000

31
core/resources-src/datafiles/thrustcurves/thrustcurve.org/Estes_F15_1.eng Normal file
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; Estes F15 RASP.ENG file made from NAR published data
; File produced by Howard Smart 7/1/2013
;The data in the PDF file on the NAR website as of today is incorrect
;It is a copy-paste of the data for the Estes E16 data - a simple error
;I made this data file as an approximation of the curve that they display
;in the PDF file, which appears to be correct
;
F15 29 114 0-2-4-6 0.06 0.103 E
0.063 2.127
0.118 4.407
0.158 8.359
0.228 13.68
0.340 20.82
0.386 26.75
0.425 25.38
0.481 22.19
0.583 17.93
0.883 16.11
1.191 14.59
1.364 15.35
1.569 15.65
1.727 14.74
2.00 14.28
2.39 13.68
2.68 13.08
2.96 13.07
3.25 13.05
3.35 13.0
3.39 7.30
3.40 0.00
;

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core/resources/datafiles/thrustcurves/thrustcurves.ser
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