S1014 (s1014-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1014 (s1014-il) Reynolds number: 50,000 Max Cl/Cd: 20.31 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1014-il-50000-n5.txt Download as CSV file: xf-s1014-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1014
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6134 0.11152 0.10380 -0.0485 1.0000 0.0937
-14.250 -0.6938 0.09148 0.08369 -0.0601 1.0000 0.0931
-14.000 -0.7607 0.07916 0.07116 -0.0660 1.0000 0.0918
-13.750 -0.7978 0.07250 0.06426 -0.0675 1.0000 0.0921
-13.500 -0.8235 0.06767 0.05919 -0.0675 1.0000 0.0930
-13.250 -0.8439 0.06371 0.05499 -0.0667 1.0000 0.0942
-13.000 -0.8629 0.06028 0.05128 -0.0652 1.0000 0.0958
-12.750 -0.8818 0.05735 0.04802 -0.0627 1.0000 0.0975
-12.500 -0.8880 0.05542 0.04598 -0.0603 1.0000 0.0995
-12.250 -0.8883 0.05435 0.04493 -0.0577 1.0000 0.1019
-12.000 -0.8984 0.05330 0.04378 -0.0536 1.0000 0.1038
-11.750 -0.9107 0.05219 0.04253 -0.0491 1.0000 0.1058
-11.500 -0.9237 0.05103 0.04118 -0.0444 1.0000 0.1080
-11.250 -0.9376 0.04985 0.03973 -0.0394 1.0000 0.1104
-11.000 -0.9402 0.04871 0.03846 -0.0357 1.0000 0.1132
-10.750 -0.9355 0.04780 0.03756 -0.0329 1.0000 0.1165
-10.500 -0.9228 0.04644 0.03602 -0.0318 0.9972 0.1215
-10.250 -0.9063 0.04496 0.03427 -0.0313 0.9939 0.1274
-10.000 -0.8842 0.04386 0.03317 -0.0313 0.9914 0.1335
-9.750 -0.8661 0.04266 0.03165 -0.0306 0.9889 0.1407
-9.500 -0.8410 0.04170 0.03080 -0.0308 0.9871 0.1481
-9.250 -0.8168 0.04073 0.02961 -0.0308 0.9852 0.1571
-9.000 -0.7913 0.03994 0.02885 -0.0309 0.9837 0.1666
-8.750 -0.7641 0.03919 0.02806 -0.0313 0.9823 0.1776
-8.500 -0.7399 0.03850 0.02729 -0.0311 0.9805 0.1899
-8.250 -0.7194 0.03784 0.02662 -0.0304 0.9783 0.2030
-8.000 -0.6995 0.03718 0.02601 -0.0297 0.9761 0.2171
-7.750 -0.6818 0.03652 0.02541 -0.0287 0.9740 0.2336
-7.500 -0.6657 0.03587 0.02482 -0.0275 0.9721 0.2523
-7.250 -0.6519 0.03520 0.02428 -0.0261 0.9704 0.2733
-7.000 -0.6402 0.03451 0.02376 -0.0243 0.9687 0.2989
-6.750 -0.6351 0.03385 0.02330 -0.0211 0.9663 0.3267
-6.500 -0.6297 0.03319 0.02291 -0.0180 0.9636 0.3633
-6.250 -0.6206 0.03269 0.02278 -0.0151 0.9613 0.4125
-6.000 -0.5884 0.03327 0.02390 -0.0141 0.9605 0.4899
-5.750 -0.5340 0.03557 0.02643 -0.0148 0.9604 0.5577
-5.500 -0.5019 0.03706 0.02784 -0.0136 0.9591 0.5956
-5.250 -0.4810 0.03795 0.02859 -0.0118 0.9571 0.6264
-5.000 -0.4648 0.03862 0.02911 -0.0096 0.9549 0.6550
-4.750 -0.4579 0.03922 0.02960 -0.0057 0.9525 0.6779
-4.500 -0.4576 0.03960 0.02988 -0.0011 0.9496 0.7007
-4.250 -0.4404 0.04034 0.03048 0.0012 0.9471 0.7200
-4.000 -0.4229 0.04098 0.03100 0.0033 0.9449 0.7385
-3.750 -0.3979 0.04167 0.03154 0.0042 0.9431 0.7554
-3.500 -0.3645 0.04236 0.03210 0.0036 0.9415 0.7710
-3.250 -0.3309 0.04292 0.03254 0.0029 0.9399 0.7857
-3.000 -0.3098 0.04324 0.03276 0.0042 0.9375 0.7999
-2.750 -0.2897 0.04346 0.03289 0.0055 0.9349 0.8139
-2.500 -0.2557 0.04365 0.03299 0.0042 0.9328 0.8250
-2.250 -0.2225 0.04371 0.03296 0.0027 0.9305 0.8344
-2.000 -0.2040 0.04374 0.03291 0.0037 0.9276 0.8457
-1.750 -0.1602 0.04373 0.03282 0.0001 0.9258 0.8521
-1.500 -0.1523 0.04369 0.03273 0.0029 0.9219 0.8622
-1.250 -0.1197 0.04360 0.03260 0.0013 0.9187 0.8680
-1.000 -0.1057 0.04359 0.03254 0.0028 0.9145 0.8766
-0.750 -0.0685 0.04353 0.03245 0.0002 0.9116 0.8813
-0.500 -0.0387 0.04351 0.03241 -0.0012 0.9081 0.8869
-0.250 -0.0347 0.04349 0.03238 0.0023 0.9021 0.8941
0.000 0.0000 0.04344 0.03233 0.0000 0.8979 0.8979
0.250 0.0346 0.04349 0.03238 -0.0023 0.8942 0.9021
0.500 0.0388 0.04351 0.03241 0.0012 0.8869 0.9081
0.750 0.0683 0.04352 0.03244 -0.0001 0.8813 0.9116
1.000 0.1058 0.04358 0.03254 -0.0029 0.8766 0.9145
1.250 0.1198 0.04359 0.03259 -0.0013 0.8680 0.9187
1.500 0.1522 0.04368 0.03272 -0.0029 0.8622 0.9219
1.750 0.1604 0.04372 0.03281 -0.0002 0.8521 0.9259
2.000 0.2040 0.04373 0.03290 -0.0037 0.8457 0.9277
2.250 0.2224 0.04371 0.03295 -0.0027 0.8345 0.9305
2.500 0.2558 0.04364 0.03298 -0.0042 0.8251 0.9328
2.750 0.2893 0.04345 0.03288 -0.0054 0.8140 0.9349
3.000 0.3094 0.04323 0.03275 -0.0042 0.8000 0.9376
3.250 0.3307 0.04291 0.03253 -0.0029 0.7858 0.9400
3.500 0.3645 0.04235 0.03209 -0.0037 0.7711 0.9415
3.750 0.3982 0.04165 0.03153 -0.0042 0.7554 0.9431
4.000 0.4231 0.04097 0.03099 -0.0033 0.7387 0.9449
4.250 0.4404 0.04033 0.03047 -0.0012 0.7201 0.9471
4.500 0.4573 0.03961 0.02988 0.0011 0.7008 0.9496
4.750 0.4583 0.03921 0.02959 0.0057 0.6781 0.9525
5.250 0.4812 0.03793 0.02856 0.0118 0.6264 0.9571
5.500 0.5020 0.03705 0.02782 0.0136 0.5957 0.9591
5.750 0.5342 0.03555 0.02641 0.0147 0.5577 0.9604
6.000 0.5884 0.03326 0.02388 0.0141 0.4899 0.9606
6.250 0.6207 0.03268 0.02275 0.0151 0.4124 0.9614
6.500 0.6298 0.03317 0.02289 0.0180 0.3632 0.9636
6.750 0.6352 0.03384 0.02328 0.0211 0.3265 0.9663
7.000 0.6402 0.03449 0.02374 0.0243 0.2986 0.9688
7.250 0.6523 0.03518 0.02426 0.0260 0.2733 0.9705
7.500 0.6659 0.03586 0.02481 0.0275 0.2519 0.9722
7.750 0.6821 0.03651 0.02539 0.0287 0.2335 0.9740
8.000 0.7000 0.03717 0.02600 0.0296 0.2170 0.9762
8.250 0.7199 0.03783 0.02659 0.0303 0.2030 0.9784
8.500 0.7404 0.03848 0.02727 0.0310 0.1899 0.9806
8.750 0.7645 0.03917 0.02804 0.0312 0.1776 0.9823
9.000 0.7920 0.03992 0.02883 0.0308 0.1666 0.9837
9.250 0.8175 0.04072 0.02960 0.0306 0.1571 0.9853
9.500 0.8412 0.04169 0.03078 0.0307 0.1480 0.9871
9.750 0.8661 0.04265 0.03165 0.0306 0.1405 0.9890
10.000 0.8845 0.04385 0.03316 0.0312 0.1335 0.9915
10.250 0.9065 0.04493 0.03424 0.0312 0.1273 0.9940
10.500 0.9234 0.04644 0.03602 0.0317 0.1214 0.9973
10.750 0.9358 0.04779 0.03755 0.0329 0.1165 1.0000
11.000 0.9399 0.04865 0.03840 0.0358 0.1131 1.0000
11.250 0.9378 0.04984 0.03971 0.0394 0.1104 1.0000
11.500 0.9238 0.05101 0.04116 0.0444 0.1079 1.0000
11.750 0.9107 0.05216 0.04249 0.0491 0.1058 1.0000
12.000 0.8984 0.05326 0.04375 0.0536 0.1038 1.0000
12.250 0.8885 0.05431 0.04488 0.0577 0.1018 1.0000
12.500 0.8887 0.05538 0.04593 0.0603 0.0994 1.0000
12.750 0.8814 0.05735 0.04803 0.0627 0.0974 1.0000
13.000 0.8634 0.06029 0.05129 0.0651 0.0958 1.0000
13.250 0.8448 0.06371 0.05498 0.0666 0.0942 1.0000
13.500 0.8241 0.06768 0.05920 0.0674 0.0928 1.0000
13.750 0.7989 0.07251 0.06427 0.0673 0.0920 1.0000
14.000 0.7622 0.07912 0.07111 0.0658 0.0917 1.0000
14.250 0.6946 0.09155 0.08376 0.0599 0.0930 1.0000
14.500 0.6141 0.11168 0.10397 0.0482 0.0936 1.0000
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