S1014 (s1014-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1014 (s1014-il) Reynolds number: 100,000 Max Cl/Cd: 23.23 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1014-il-100000-n5.txt Download as CSV file: xf-s1014-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8655 0.09391 0.08792 -0.0539 1.0000 0.0469
-16.750 -0.8816 0.08760 0.08151 -0.0575 1.0000 0.0475
-16.500 -0.8909 0.08269 0.07651 -0.0600 1.0000 0.0482
-16.250 -0.9040 0.07743 0.07110 -0.0625 1.0000 0.0487
-16.000 -0.9143 0.07291 0.06645 -0.0645 1.0000 0.0495
-15.750 -0.9249 0.06862 0.06199 -0.0660 1.0000 0.0503
-15.500 -0.9348 0.06459 0.05777 -0.0670 1.0000 0.0513
-15.250 -0.9434 0.06090 0.05384 -0.0676 1.0000 0.0523
-15.000 -0.9507 0.05747 0.05015 -0.0678 1.0000 0.0535
-14.750 -0.9562 0.05431 0.04668 -0.0676 1.0000 0.0548
-14.500 -0.9509 0.05236 0.04473 -0.0676 1.0000 0.0562
-14.250 -0.9457 0.05056 0.04290 -0.0674 1.0000 0.0578
-14.000 -0.9409 0.04868 0.04091 -0.0670 1.0000 0.0594
-13.750 -0.9368 0.04678 0.03882 -0.0665 1.0000 0.0615
-13.500 -0.9293 0.04481 0.03653 -0.0665 0.9757 0.0639
-13.250 -0.9131 0.04330 0.03500 -0.0673 0.9652 0.0660
-13.000 -0.8980 0.04187 0.03349 -0.0680 0.9577 0.0687
-12.750 -0.8823 0.04040 0.03182 -0.0683 0.9519 0.0719
-12.500 -0.8657 0.03899 0.03020 -0.0685 0.9467 0.0751
-12.250 -0.8491 0.03784 0.02903 -0.0687 0.9423 0.0780
-12.000 -0.8325 0.03674 0.02781 -0.0686 0.9384 0.0815
-11.750 -0.8154 0.03569 0.02653 -0.0683 0.9345 0.0855
-11.500 -0.7985 0.03468 0.02555 -0.0680 0.9311 0.0890
-11.250 -0.7811 0.03379 0.02458 -0.0677 0.9280 0.0931
-11.000 -0.7620 0.03296 0.02354 -0.0674 0.9254 0.0981
-10.750 -0.7447 0.03209 0.02271 -0.0670 0.9227 0.1022
-10.500 -0.7271 0.03134 0.02190 -0.0665 0.9199 0.1076
-10.250 -0.7079 0.03062 0.02110 -0.0660 0.9172 0.1132
-10.000 -0.6907 0.02990 0.02037 -0.0654 0.9144 0.1186
-9.750 -0.6710 0.02929 0.01964 -0.0649 0.9121 0.1255
-9.500 -0.6535 0.02859 0.01900 -0.0642 0.9100 0.1319
-9.250 -0.6340 0.02804 0.01836 -0.0637 0.9082 0.1400
-9.000 -0.6168 0.02741 0.01779 -0.0629 0.9061 0.1477
-8.750 -0.5978 0.02691 0.01725 -0.0623 0.9042 0.1574
-8.500 -0.5805 0.02635 0.01674 -0.0615 0.9023 0.1673
-8.250 -0.5628 0.02584 0.01626 -0.0606 0.9005 0.1788
-8.000 -0.5449 0.02537 0.01581 -0.0598 0.8988 0.1923
-7.750 -0.5269 0.02490 0.01539 -0.0589 0.8972 0.2077
-7.500 -0.5093 0.02442 0.01499 -0.0580 0.8955 0.2266
-7.250 -0.4921 0.02396 0.01463 -0.0569 0.8938 0.2488
-7.000 -0.4769 0.02353 0.01433 -0.0555 0.8918 0.2749
-6.750 -0.4631 0.02312 0.01410 -0.0539 0.8899 0.3069
-6.500 -0.4509 0.02272 0.01392 -0.0520 0.8880 0.3459
-6.250 -0.4400 0.02235 0.01380 -0.0498 0.8861 0.3915
-6.000 -0.4273 0.02210 0.01388 -0.0474 0.8844 0.4482
-5.750 -0.3948 0.02256 0.01476 -0.0471 0.8837 0.5186
-5.500 -0.3416 0.02411 0.01653 -0.0489 0.8838 0.5742
-5.250 -0.3068 0.02510 0.01754 -0.0489 0.8827 0.6039
-5.000 -0.2808 0.02577 0.01817 -0.0479 0.8812 0.6256
-4.750 -0.2610 0.02623 0.01855 -0.0464 0.8798 0.6443
-4.500 -0.2464 0.02656 0.01881 -0.0442 0.8783 0.6627
-4.250 -0.2393 0.02687 0.01907 -0.0410 0.8762 0.6797
-3.750 -0.2252 0.02790 0.02003 -0.0338 0.8703 0.7065
-3.500 -0.2175 0.02835 0.02044 -0.0303 0.8676 0.7189
-3.250 -0.2135 0.02867 0.02071 -0.0261 0.8647 0.7320
-3.000 -0.2142 0.02892 0.02091 -0.0212 0.8623 0.7458
-2.750 -0.1565 0.02979 0.02173 -0.0255 0.8624 0.7503
-2.500 -0.1815 0.03023 0.02217 -0.0164 0.8567 0.7636
-2.250 -0.1266 0.03091 0.02282 -0.0206 0.8566 0.7681
-2.000 -0.1426 0.03116 0.02306 -0.0129 0.8512 0.7804
-1.750 -0.0968 0.03152 0.02338 -0.0160 0.8503 0.7837
-1.500 -0.1007 0.03149 0.02331 -0.0106 0.8467 0.7950
-1.250 -0.0576 0.03166 0.02345 -0.0133 0.8458 0.7975
-0.750 -0.0690 0.03205 0.02384 -0.0019 0.8344 0.8129
-0.500 -0.0308 0.03215 0.02393 -0.0039 0.8324 0.8150
-0.250 0.0057 0.03217 0.02395 -0.0057 0.8306 0.8175
0.000 -0.0402 0.03211 0.02389 0.0071 0.8205 0.8289
0.250 -0.0057 0.03217 0.02395 0.0057 0.8175 0.8306
0.500 0.0309 0.03214 0.02393 0.0039 0.8150 0.8324
0.750 0.0688 0.03204 0.02384 0.0019 0.8129 0.8344
1.250 0.0577 0.03165 0.02345 0.0133 0.7975 0.8458
1.500 0.1005 0.03150 0.02332 0.0106 0.7949 0.8468
1.750 0.0972 0.03152 0.02338 0.0159 0.7837 0.8503
2.000 0.1426 0.03116 0.02306 0.0129 0.7804 0.8512
2.250 0.1264 0.03091 0.02282 0.0206 0.7681 0.8566
2.500 0.1809 0.03023 0.02218 0.0164 0.7637 0.8568
2.750 0.1563 0.02980 0.02173 0.0255 0.7503 0.8624
3.000 0.2144 0.02891 0.02090 0.0211 0.7458 0.8623
3.250 0.2136 0.02866 0.02070 0.0261 0.7320 0.8647
3.500 0.2173 0.02836 0.02045 0.0303 0.7190 0.8677
3.750 0.2254 0.02790 0.02003 0.0338 0.7066 0.8703
4.000 0.2556 0.02708 0.01927 0.0340 0.6981 0.8715
4.250 0.2412 0.02684 0.01905 0.0407 0.6803 0.8761
4.500 0.2465 0.02655 0.01881 0.0442 0.6627 0.8783
4.750 0.2612 0.02623 0.01855 0.0464 0.6445 0.8798
5.000 0.2810 0.02576 0.01815 0.0479 0.6255 0.8812
5.250 0.3069 0.02509 0.01753 0.0488 0.6037 0.8828
5.500 0.3420 0.02408 0.01651 0.0488 0.5740 0.8838
5.750 0.3952 0.02255 0.01475 0.0470 0.5181 0.8837
6.000 0.4274 0.02210 0.01388 0.0474 0.4479 0.8844
6.250 0.4400 0.02235 0.01379 0.0497 0.3912 0.8861
6.500 0.4511 0.02271 0.01391 0.0520 0.3459 0.8880
6.750 0.4633 0.02312 0.01409 0.0539 0.3067 0.8899
7.000 0.4771 0.02353 0.01432 0.0555 0.2748 0.8918
7.250 0.4923 0.02395 0.01462 0.0569 0.2487 0.8938
7.500 0.5095 0.02442 0.01499 0.0580 0.2261 0.8955
7.750 0.5272 0.02489 0.01538 0.0589 0.2077 0.8972
8.000 0.5451 0.02536 0.01580 0.0597 0.1922 0.8988
8.250 0.5631 0.02583 0.01625 0.0606 0.1788 0.9005
8.500 0.5809 0.02635 0.01673 0.0614 0.1673 0.9023
8.750 0.5981 0.02690 0.01724 0.0622 0.1574 0.9042
9.000 0.6172 0.02740 0.01778 0.0629 0.1477 0.9062
9.250 0.6344 0.02803 0.01835 0.0636 0.1399 0.9082
9.500 0.6539 0.02859 0.01899 0.0641 0.1318 0.9101
9.750 0.6714 0.02928 0.01963 0.0648 0.1253 0.9121
10.000 0.6912 0.02988 0.02036 0.0653 0.1186 0.9145
10.250 0.7083 0.03061 0.02108 0.0659 0.1131 0.9172
10.500 0.7276 0.03133 0.02190 0.0664 0.1075 0.9200
10.750 0.7453 0.03208 0.02271 0.0669 0.1022 0.9228
11.000 0.7624 0.03295 0.02354 0.0673 0.0979 0.9255
11.250 0.7820 0.03379 0.02458 0.0676 0.0931 0.9280
11.500 0.7990 0.03467 0.02554 0.0679 0.0889 0.9312
11.750 0.8161 0.03568 0.02653 0.0682 0.0854 0.9346
12.000 0.8333 0.03673 0.02781 0.0685 0.0813 0.9385
12.250 0.8498 0.03782 0.02901 0.0686 0.0779 0.9425
12.500 0.8666 0.03898 0.03019 0.0684 0.0750 0.9469
12.750 0.8828 0.04039 0.03182 0.0682 0.0717 0.9521
13.000 0.8990 0.04185 0.03347 0.0678 0.0686 0.9580
13.250 0.9146 0.04329 0.03500 0.0671 0.0661 0.9656
13.500 0.9302 0.04484 0.03657 0.0663 0.0638 0.9764
13.750 0.9379 0.04677 0.03881 0.0663 0.0615 1.0000
14.000 0.9422 0.04867 0.04089 0.0669 0.0594 1.0000
14.250 0.9468 0.05053 0.04286 0.0672 0.0577 1.0000
14.500 0.9523 0.05233 0.04470 0.0674 0.0562 1.0000
14.750 0.9588 0.05424 0.04659 0.0674 0.0549 1.0000
15.000 0.9521 0.05745 0.05013 0.0676 0.0535 1.0000
15.250 0.9447 0.06088 0.05382 0.0674 0.0522 1.0000
15.500 0.9363 0.06455 0.05772 0.0668 0.0512 1.0000
15.750 0.9266 0.06854 0.06190 0.0658 0.0502 1.0000
16.000 0.9155 0.07294 0.06647 0.0643 0.0495 1.0000
16.250 0.9050 0.07748 0.07115 0.0623 0.0487 1.0000
16.500 0.8978 0.08179 0.07555 0.0603 0.0479 1.0000
16.750 0.8867 0.08698 0.08085 0.0576 0.0474 1.0000
17.000 0.8690 0.09354 0.08754 0.0540 0.0470 1.0000
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Polar data table (+)
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