NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il) Reynolds number: 200,000 Max Cl/Cd: 44.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20614-il-200000-n5.txt Download as CSV file: xf-sc20614-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0614 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9142 0.09122 0.08596 -0.0521 1.0000 0.0346
-16.500 -0.9533 0.08016 0.07460 -0.0590 1.0000 0.0347
-16.250 -0.9745 0.07312 0.06733 -0.0629 1.0000 0.0348
-16.000 -0.9892 0.06757 0.06158 -0.0657 1.0000 0.0351
-15.750 -1.0000 0.06294 0.05676 -0.0677 1.0000 0.0354
-15.500 -1.0081 0.05892 0.05256 -0.0692 1.0000 0.0357
-15.250 -1.0142 0.05542 0.04887 -0.0701 1.0000 0.0361
-15.000 -1.0179 0.05230 0.04557 -0.0706 1.0000 0.0365
-14.750 -1.0199 0.04948 0.04256 -0.0708 1.0000 0.0369
-14.500 -1.0196 0.04699 0.03988 -0.0708 1.0000 0.0373
-14.250 -1.0139 0.04521 0.03808 -0.0705 1.0000 0.0377
-14.000 -1.0081 0.04354 0.03637 -0.0702 1.0000 0.0382
-13.750 -1.0021 0.04196 0.03474 -0.0697 1.0000 0.0387
-13.500 -0.9961 0.04046 0.03318 -0.0689 1.0000 0.0393
-13.250 -0.9903 0.03902 0.03166 -0.0680 1.0000 0.0400
-13.000 -0.9847 0.03764 0.03019 -0.0668 1.0000 0.0407
-12.750 -0.9793 0.03634 0.02878 -0.0652 1.0000 0.0415
-12.500 -0.9741 0.03513 0.02743 -0.0634 1.0000 0.0422
-12.250 -0.9693 0.03403 0.02628 -0.0613 1.0000 0.0428
-12.000 -0.9666 0.03309 0.02534 -0.0588 1.0000 0.0433
-11.750 -0.9667 0.03226 0.02450 -0.0557 1.0000 0.0439
-11.500 -0.9673 0.03147 0.02370 -0.0523 1.0000 0.0445
-11.250 -0.9624 0.03062 0.02281 -0.0500 1.0000 0.0452
-11.000 -0.9554 0.02978 0.02191 -0.0479 1.0000 0.0462
-10.750 -0.9462 0.02896 0.02102 -0.0461 1.0000 0.0473
-10.500 -0.9350 0.02816 0.02013 -0.0445 1.0000 0.0485
-10.250 -0.9168 0.02728 0.01928 -0.0444 0.9991 0.0498
-10.000 -0.8876 0.02643 0.01840 -0.0463 0.9967 0.0515
-9.750 -0.8579 0.02563 0.01753 -0.0480 0.9944 0.0535
-9.500 -0.8277 0.02482 0.01666 -0.0497 0.9923 0.0555
-9.250 -0.7988 0.02403 0.01588 -0.0513 0.9893 0.0573
-9.000 -0.7684 0.02337 0.01519 -0.0530 0.9865 0.0598
-8.750 -0.7371 0.02274 0.01449 -0.0546 0.9841 0.0625
-8.500 -0.7049 0.02204 0.01383 -0.0567 0.9821 0.0652
-8.250 -0.6718 0.02146 0.01321 -0.0588 0.9803 0.0683
-8.000 -0.6436 0.02089 0.01261 -0.0597 0.9764 0.0712
-7.750 -0.6123 0.02027 0.01203 -0.0614 0.9734 0.0746
-7.500 -0.5796 0.01978 0.01151 -0.0632 0.9711 0.0786
-7.250 -0.5456 0.01919 0.01096 -0.0654 0.9693 0.0828
-7.000 -0.5103 0.01870 0.01047 -0.0677 0.9678 0.0879
-6.750 -0.4805 0.01821 0.01000 -0.0689 0.9639 0.0930
-6.500 -0.4483 0.01774 0.00955 -0.0705 0.9607 0.0994
-6.250 -0.4140 0.01724 0.00910 -0.0726 0.9584 0.1072
-6.000 -0.3785 0.01678 0.00869 -0.0749 0.9565 0.1171
-5.750 -0.3417 0.01630 0.00828 -0.0775 0.9551 0.1315
-5.500 -0.3037 0.01577 0.00787 -0.0804 0.9539 0.1521
-5.250 -0.2669 0.01523 0.00749 -0.0831 0.9519 0.1821
-5.000 -0.2339 0.01466 0.00714 -0.0851 0.9479 0.2263
-4.750 -0.1940 0.01387 0.00672 -0.0889 0.9461 0.2988
-4.500 -0.1510 0.01298 0.00636 -0.0935 0.9450 0.4046
-4.250 -0.1147 0.01270 0.00658 -0.0955 0.9431 0.5084
-4.000 -0.0817 0.01281 0.00685 -0.0962 0.9409 0.5507
-3.750 -0.0451 0.01285 0.00686 -0.0979 0.9391 0.5777
-3.500 -0.0132 0.01295 0.00696 -0.0986 0.9359 0.5930
-3.250 0.0147 0.01311 0.00713 -0.0984 0.9311 0.6037
-3.000 0.0468 0.01325 0.00727 -0.0990 0.9280 0.6165
-2.750 0.0808 0.01338 0.00738 -0.1001 0.9256 0.6289
-2.500 0.1109 0.01362 0.00768 -0.0999 0.9232 0.6357
-2.250 0.1414 0.01381 0.00786 -0.1002 0.9190 0.6467
-2.000 0.1649 0.01416 0.00828 -0.0985 0.9134 0.6522
-1.750 0.1980 0.01418 0.00829 -0.0994 0.9099 0.6579
-1.500 0.2349 0.01405 0.00814 -0.1012 0.9070 0.6629
-1.250 0.2602 0.01415 0.00829 -0.1001 0.8992 0.6654
-1.000 0.2923 0.01403 0.00819 -0.1004 0.8921 0.6682
-0.750 0.3231 0.01382 0.00798 -0.1005 0.8800 0.6710
-0.500 0.3566 0.01352 0.00763 -0.1012 0.8655 0.6738
-0.250 0.3914 0.01320 0.00724 -0.1023 0.8472 0.6777
0.000 0.4197 0.01309 0.00711 -0.1017 0.8276 0.6791
0.250 0.4479 0.01303 0.00704 -0.1012 0.8069 0.6807
0.500 0.4768 0.01299 0.00696 -0.1009 0.7853 0.6824
0.750 0.5055 0.01297 0.00687 -0.1006 0.7553 0.6842
1.000 0.5339 0.01300 0.00675 -0.1002 0.7065 0.6861
1.250 0.5585 0.01335 0.00659 -0.0991 0.5991 0.6883
1.500 0.5773 0.01427 0.00675 -0.0974 0.4631 0.6909
1.750 0.5995 0.01507 0.00702 -0.0967 0.3646 0.6937
2.000 0.6204 0.01578 0.00738 -0.0954 0.2877 0.6951
2.250 0.6433 0.01638 0.00770 -0.0946 0.2331 0.6966
2.500 0.6675 0.01688 0.00800 -0.0940 0.1934 0.6981
3.000 0.7186 0.01774 0.00859 -0.0934 0.1427 0.7018
3.250 0.7452 0.01811 0.00889 -0.0932 0.1264 0.7040
3.500 0.7723 0.01849 0.00918 -0.0933 0.1135 0.7064
3.750 0.8000 0.01889 0.00949 -0.0935 0.1036 0.7090
4.000 0.8254 0.01925 0.00986 -0.0930 0.0967 0.7104
4.250 0.8493 0.01972 0.01028 -0.0923 0.0909 0.7118
4.500 0.8742 0.02009 0.01071 -0.0916 0.0859 0.7134
4.750 0.8983 0.02056 0.01116 -0.0910 0.0815 0.7153
5.000 0.9228 0.02102 0.01163 -0.0904 0.0778 0.7175
5.250 0.9479 0.02146 0.01209 -0.0899 0.0741 0.7200
5.500 0.9722 0.02202 0.01260 -0.0895 0.0711 0.7226
5.750 0.9982 0.02248 0.01310 -0.0893 0.0683 0.7255
6.000 1.0210 0.02296 0.01363 -0.0883 0.0657 0.7271
6.250 1.0433 0.02351 0.01419 -0.0874 0.0634 0.7287
6.500 1.0658 0.02409 0.01481 -0.0864 0.0612 0.7305
6.750 1.0889 0.02462 0.01541 -0.0856 0.0590 0.7325
7.000 1.1116 0.02518 0.01600 -0.0848 0.0570 0.7347
7.250 1.1334 0.02585 0.01666 -0.0840 0.0554 0.7371
7.500 1.1563 0.02653 0.01740 -0.0832 0.0538 0.7397
7.750 1.1787 0.02719 0.01813 -0.0824 0.0519 0.7422
8.000 1.1986 0.02782 0.01883 -0.0811 0.0504 0.7440
8.250 1.2175 0.02853 0.01956 -0.0797 0.0490 0.7460
8.500 1.2368 0.02934 0.02045 -0.0784 0.0477 0.7482
8.750 1.2563 0.03014 0.02138 -0.0772 0.0463 0.7506
9.000 1.2752 0.03097 0.02229 -0.0759 0.0451 0.7531
9.250 1.2931 0.03180 0.02317 -0.0745 0.0441 0.7557
9.500 1.3091 0.03266 0.02405 -0.0729 0.0433 0.7585
9.750 1.3218 0.03363 0.02506 -0.0706 0.0425 0.7602
10.000 1.3365 0.03465 0.02628 -0.0687 0.0416 0.7622
10.250 1.3506 0.03572 0.02752 -0.0668 0.0406 0.7644
10.500 1.3641 0.03680 0.02872 -0.0650 0.0397 0.7671
10.750 1.3770 0.03789 0.02992 -0.0632 0.0389 0.7700
11.000 1.3893 0.03902 0.03111 -0.0615 0.0382 0.7731
11.250 1.4008 0.04023 0.03238 -0.0598 0.0377 0.7757
11.500 1.4104 0.04161 0.03381 -0.0578 0.0372 0.7776
11.750 1.4180 0.04329 0.03574 -0.0557 0.0367 0.7797
12.000 1.4243 0.04510 0.03778 -0.0537 0.0361 0.7820
12.250 1.4292 0.04703 0.03992 -0.0517 0.0356 0.7844
12.500 1.4327 0.04909 0.04217 -0.0499 0.0351 0.7870
12.750 1.4350 0.05128 0.04454 -0.0483 0.0347 0.7897
13.000 1.4361 0.05360 0.04702 -0.0468 0.0343 0.7922
13.250 1.4357 0.05600 0.04959 -0.0453 0.0339 0.7941
13.500 1.4345 0.05854 0.05228 -0.0441 0.0336 0.7962
13.750 1.4327 0.06124 0.05512 -0.0432 0.0333 0.7984
14.000 1.4301 0.06416 0.05816 -0.0426 0.0330 0.8008
14.250 1.4271 0.06725 0.06136 -0.0424 0.0328 0.8034
14.500 1.4225 0.07071 0.06492 -0.0425 0.0325 0.8060
14.750 1.4094 0.07557 0.07000 -0.0433 0.0323 0.8084
15.000 1.3882 0.08184 0.07659 -0.0453 0.0321 0.8099
15.250 1.3632 0.08943 0.08449 -0.0487 0.0320 0.8113
15.500 1.3326 0.09895 0.09433 -0.0542 0.0319 0.8125
15.750 1.2898 0.11216 0.10790 -0.0631 0.0319 0.8131
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Polar data table (+)
Polar graphs
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