S1016 (s1016-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1016 (s1016-il) Reynolds number: 200,000 Max Cl/Cd: 30.19 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1016-il-200000-n5.txt Download as CSV file: xf-s1016-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1016
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.9721 0.10514 0.10004 -0.0471 1.0000 0.0365
-19.250 -0.9815 0.09968 0.09448 -0.0502 1.0000 0.0371
-19.000 -0.9902 0.09443 0.08912 -0.0531 1.0000 0.0378
-18.750 -0.9987 0.08933 0.08389 -0.0559 1.0000 0.0385
-18.500 -1.0062 0.08447 0.07889 -0.0584 1.0000 0.0394
-18.250 -1.0123 0.07993 0.07419 -0.0607 1.0000 0.0403
-18.000 -1.0168 0.07577 0.06990 -0.0627 1.0000 0.0411
-17.500 -1.0240 0.06808 0.06205 -0.0666 0.9575 0.0427
-17.250 -1.0214 0.06440 0.05824 -0.0692 0.9472 0.0440
-16.750 -1.0142 0.05821 0.05169 -0.0726 0.9331 0.0467
-16.500 -1.0116 0.05541 0.04877 -0.0736 0.9279 0.0479
-16.250 -1.0095 0.05273 0.04602 -0.0744 0.9236 0.0491
-16.000 -1.0057 0.05040 0.04358 -0.0748 0.9198 0.0505
-15.750 -1.0000 0.04833 0.04139 -0.0750 0.9164 0.0522
-15.500 -0.9930 0.04645 0.03936 -0.0751 0.9134 0.0539
-15.250 -0.9881 0.04450 0.03734 -0.0749 0.9107 0.0555
-14.750 -0.9742 0.04114 0.03382 -0.0744 0.9062 0.0592
-14.500 -0.9643 0.03976 0.03232 -0.0740 0.9039 0.0615
-14.250 -0.9556 0.03834 0.03083 -0.0735 0.9014 0.0635
-14.000 -0.9475 0.03697 0.02942 -0.0728 0.8992 0.0656
-13.750 -0.9372 0.03577 0.02815 -0.0721 0.8972 0.0680
-13.500 -0.9247 0.03476 0.02701 -0.0715 0.8955 0.0708
-13.250 -0.9148 0.03364 0.02585 -0.0705 0.8939 0.0733
-12.750 -0.8910 0.03171 0.02381 -0.0688 0.8910 0.0791
-12.500 -0.8761 0.03090 0.02290 -0.0682 0.8896 0.0824
-12.250 -0.8644 0.02994 0.02195 -0.0673 0.8882 0.0855
-12.000 -0.8501 0.02915 0.02111 -0.0665 0.8868 0.0891
-11.750 -0.8335 0.02849 0.02036 -0.0658 0.8855 0.0931
-11.500 -0.8205 0.02766 0.01955 -0.0648 0.8841 0.0967
-11.250 -0.8052 0.02699 0.01883 -0.0639 0.8829 0.1010
-11.000 -0.7877 0.02643 0.01819 -0.0632 0.8817 0.1055
-10.750 -0.7737 0.02572 0.01751 -0.0621 0.8805 0.1099
-10.500 -0.7573 0.02515 0.01690 -0.0612 0.8793 0.1151
-10.250 -0.7405 0.02463 0.01632 -0.0602 0.8779 0.1202
-10.000 -0.7253 0.02405 0.01575 -0.0591 0.8766 0.1256
-9.750 -0.7071 0.02361 0.01525 -0.0582 0.8756 0.1317
-9.500 -0.6904 0.02305 0.01473 -0.0574 0.8746 0.1381
-9.250 -0.6720 0.02259 0.01425 -0.0566 0.8735 0.1452
-9.000 -0.6543 0.02212 0.01379 -0.0558 0.8724 0.1519
-8.750 -0.6358 0.02169 0.01337 -0.0550 0.8713 0.1599
-8.500 -0.6180 0.02125 0.01296 -0.0541 0.8702 0.1684
-8.250 -0.5991 0.02087 0.01258 -0.0533 0.8691 0.1781
-8.000 -0.5820 0.02044 0.01220 -0.0523 0.8678 0.1879
-7.750 -0.5639 0.02008 0.01185 -0.0512 0.8663 0.1987
-7.500 -0.5460 0.01971 0.01150 -0.0502 0.8649 0.2113
-7.250 -0.5293 0.01933 0.01117 -0.0489 0.8638 0.2243
-7.000 -0.5124 0.01896 0.01087 -0.0477 0.8627 0.2387
-6.750 -0.4959 0.01860 0.01057 -0.0463 0.8616 0.2548
-6.500 -0.4799 0.01826 0.01028 -0.0449 0.8605 0.2722
-6.250 -0.4650 0.01792 0.01001 -0.0431 0.8593 0.2918
-6.000 -0.4500 0.01758 0.00979 -0.0416 0.8574 0.3143
-5.750 -0.4370 0.01724 0.00957 -0.0397 0.8558 0.3376
-5.500 -0.4252 0.01693 0.00938 -0.0375 0.8537 0.3633
-5.250 -0.4164 0.01662 0.00921 -0.0346 0.8512 0.3909
-4.750 -0.4055 0.01616 0.00903 -0.0272 0.8468 0.4518
-4.500 -0.4004 0.01593 0.00896 -0.0231 0.8446 0.4879
-4.250 -0.3897 0.01572 0.00895 -0.0200 0.8431 0.5276
-4.000 -0.3757 0.01568 0.00917 -0.0175 0.8405 0.5717
-3.750 -0.3439 0.01593 0.00972 -0.0179 0.8388 0.6196
-3.500 -0.2735 0.01672 0.01067 -0.0246 0.8400 0.6545
-3.250 -0.2310 0.01751 0.01151 -0.0265 0.8389 0.6725
-3.000 -0.2067 0.01803 0.01206 -0.0255 0.8363 0.6872
-2.750 -0.1939 0.01831 0.01233 -0.0227 0.8332 0.7015
-2.500 -0.1920 0.01834 0.01234 -0.0180 0.8298 0.7171
-2.250 -0.1840 0.01833 0.01229 -0.0143 0.8274 0.7308
-2.000 -0.1839 0.01844 0.01236 -0.0095 0.8229 0.7438
-1.750 -0.1634 0.01893 0.01286 -0.0079 0.8184 0.7498
-1.500 -0.1533 0.01891 0.01280 -0.0047 0.8144 0.7601
-1.250 -0.1187 0.01926 0.01314 -0.0054 0.8125 0.7641
-1.000 -0.1056 0.01906 0.01287 -0.0026 0.8100 0.7749
-0.750 -0.0653 0.01939 0.01321 -0.0042 0.8088 0.7775
-0.500 -0.0517 0.01993 0.01381 -0.0015 0.8004 0.7819
-0.250 -0.0409 0.01963 0.01346 0.0016 0.7958 0.7918
0.000 0.0000 0.01970 0.01353 0.0000 0.7938 0.7938
0.250 0.0409 0.01963 0.01346 -0.0016 0.7918 0.7958
0.500 0.0518 0.01993 0.01380 0.0015 0.7819 0.8004
0.750 0.0654 0.01938 0.01321 0.0042 0.7775 0.8088
1.000 0.1055 0.01906 0.01287 0.0026 0.7749 0.8100
1.250 0.1188 0.01925 0.01314 0.0054 0.7641 0.8125
1.500 0.1531 0.01892 0.01281 0.0047 0.7601 0.8144
1.750 0.1634 0.01893 0.01286 0.0079 0.7498 0.8184
2.000 0.1837 0.01844 0.01237 0.0095 0.7439 0.8229
2.250 0.1840 0.01833 0.01228 0.0143 0.7308 0.8273
2.500 0.1920 0.01834 0.01233 0.0180 0.7170 0.8298
2.750 0.1941 0.01831 0.01234 0.0227 0.7017 0.8332
3.000 0.2067 0.01804 0.01207 0.0255 0.6875 0.8363
3.250 0.2309 0.01751 0.01152 0.0265 0.6728 0.8389
3.500 0.2727 0.01673 0.01069 0.0247 0.6549 0.8401
3.750 0.3455 0.01592 0.00969 0.0177 0.6179 0.8386
4.000 0.3758 0.01568 0.00917 0.0175 0.5716 0.8406
4.250 0.3899 0.01571 0.00895 0.0199 0.5280 0.8431
4.500 0.4002 0.01593 0.00896 0.0231 0.4872 0.8446
4.750 0.4057 0.01616 0.00902 0.0272 0.4519 0.8468
5.250 0.4163 0.01662 0.00920 0.0347 0.3904 0.8512
5.500 0.4255 0.01693 0.00938 0.0375 0.3636 0.8538
5.750 0.4371 0.01724 0.00957 0.0397 0.3375 0.8558
6.000 0.4502 0.01758 0.00978 0.0416 0.3143 0.8574
6.250 0.4652 0.01791 0.01001 0.0431 0.2917 0.8593
6.500 0.4802 0.01825 0.01028 0.0448 0.2724 0.8605
6.750 0.4961 0.01860 0.01056 0.0463 0.2545 0.8616
7.000 0.5126 0.01896 0.01086 0.0476 0.2385 0.8627
7.250 0.5296 0.01932 0.01117 0.0489 0.2243 0.8638
7.500 0.5464 0.01971 0.01150 0.0501 0.2110 0.8650
7.750 0.5643 0.02007 0.01184 0.0512 0.1988 0.8664
8.000 0.5823 0.02044 0.01219 0.0522 0.1879 0.8679
8.250 0.5995 0.02087 0.01257 0.0532 0.1780 0.8691
8.500 0.6185 0.02124 0.01294 0.0540 0.1686 0.8702
8.750 0.6362 0.02168 0.01336 0.0549 0.1601 0.8713
9.000 0.6546 0.02211 0.01379 0.0557 0.1518 0.8724
9.250 0.6725 0.02258 0.01425 0.0565 0.1449 0.8735
9.500 0.6909 0.02304 0.01472 0.0573 0.1379 0.8746
9.750 0.7077 0.02360 0.01524 0.0581 0.1317 0.8756
10.000 0.7258 0.02404 0.01574 0.0590 0.1256 0.8766
10.250 0.7411 0.02462 0.01631 0.0601 0.1202 0.8779
10.500 0.7579 0.02514 0.01689 0.0611 0.1149 0.8793
10.750 0.7744 0.02571 0.01749 0.0620 0.1099 0.8805
11.000 0.7884 0.02642 0.01817 0.0631 0.1054 0.8817
11.250 0.8059 0.02697 0.01882 0.0638 0.1008 0.8829
11.500 0.8212 0.02765 0.01953 0.0647 0.0966 0.8842
11.750 0.8343 0.02847 0.02034 0.0657 0.0929 0.8855
12.000 0.8509 0.02913 0.02109 0.0663 0.0891 0.8868
12.250 0.8652 0.02992 0.02193 0.0672 0.0854 0.8882
12.500 0.8768 0.03088 0.02289 0.0681 0.0822 0.8897
12.750 0.8920 0.03169 0.02379 0.0687 0.0791 0.8911
13.250 0.9157 0.03362 0.02582 0.0704 0.0732 0.8939
13.500 0.9258 0.03473 0.02698 0.0713 0.0708 0.8955
13.750 0.9383 0.03575 0.02812 0.0720 0.0680 0.8972
14.000 0.9486 0.03694 0.02938 0.0726 0.0655 0.8992
14.250 0.9567 0.03831 0.03079 0.0733 0.0634 0.9016
14.500 0.9657 0.03971 0.03227 0.0739 0.0613 0.9040
14.750 0.9755 0.04111 0.03378 0.0742 0.0591 0.9063
15.250 0.9895 0.04445 0.03728 0.0747 0.0554 0.9109
15.500 0.9947 0.04639 0.03929 0.0749 0.0539 0.9136
15.750 1.0020 0.04824 0.04130 0.0748 0.0521 0.9166
16.000 1.0075 0.05033 0.04351 0.0746 0.0505 0.9201
16.250 1.0114 0.05266 0.04594 0.0742 0.0491 0.9239
16.500 1.0138 0.05532 0.04868 0.0734 0.0478 0.9283
16.750 1.0165 0.05812 0.05161 0.0724 0.0467 0.9337
17.250 1.0242 0.06432 0.05816 0.0689 0.0439 0.9482
17.500 1.0270 0.06799 0.06197 0.0662 0.0428 0.9593
18.000 1.0194 0.07564 0.06976 0.0625 0.0411 1.0000
18.250 1.0148 0.07984 0.07410 0.0605 0.0402 1.0000
18.500 1.0092 0.08430 0.07871 0.0582 0.0394 1.0000
18.750 1.0019 0.08913 0.08368 0.0557 0.0386 1.0000
19.000 0.9934 0.09423 0.08891 0.0529 0.0378 1.0000
19.250 0.9842 0.09959 0.09438 0.0499 0.0371 1.0000
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