SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 100,000 Max Cl/Cd: 55.76 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3002-il-100000-n5.txt Download as CSV file: xf-s3002-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3713 0.10969 0.10451 -0.0315 1.0000 0.0530
-9.500 -0.3790 0.10664 0.10156 -0.0358 1.0000 0.0538
-9.250 -0.3802 0.10324 0.09822 -0.0381 1.0000 0.0539
-9.000 -0.3826 0.09971 0.09477 -0.0404 1.0000 0.0540
-8.750 -0.3736 0.09527 0.09037 -0.0386 1.0000 0.0548
-8.250 -0.3813 0.08383 0.07903 -0.0422 1.0000 0.0353
-8.000 -0.3698 0.08241 0.07762 -0.0387 1.0000 0.0334
-7.750 -0.3760 0.07951 0.07481 -0.0384 1.0000 0.0323
-7.250 -0.4165 0.06818 0.06364 -0.0451 1.0000 0.0279
-7.000 -0.4240 0.06557 0.06104 -0.0441 1.0000 0.0276
-6.750 -0.4292 0.06254 0.05801 -0.0438 0.9996 0.0273
-6.500 -0.4067 0.05624 0.05149 -0.0511 0.9920 0.0266
-6.250 -0.3816 0.04956 0.04447 -0.0580 0.9847 0.0260
-6.000 -0.3568 0.04340 0.03786 -0.0631 0.9770 0.0256
-5.750 -0.3256 0.03775 0.03159 -0.0678 0.9717 0.0255
-5.500 -0.2976 0.03371 0.02693 -0.0702 0.9644 0.0267
-5.250 -0.2631 0.02994 0.02233 -0.0729 0.9596 0.0284
-5.000 -0.2319 0.02764 0.01973 -0.0745 0.9543 0.0293
-4.750 -0.1998 0.02570 0.01749 -0.0758 0.9486 0.0304
-4.500 -0.1637 0.02392 0.01539 -0.0776 0.9447 0.0323
-4.250 -0.1311 0.02253 0.01366 -0.0784 0.9391 0.0356
-4.000 -0.0993 0.02132 0.01242 -0.0794 0.9333 0.0382
-3.750 -0.0638 0.02025 0.01121 -0.0808 0.9291 0.0421
-3.500 -0.0346 0.01934 0.01029 -0.0812 0.9220 0.0466
-3.250 -0.0017 0.01854 0.00943 -0.0821 0.9161 0.0518
-3.000 0.0319 0.01779 0.00867 -0.0833 0.9108 0.0602
-2.750 0.0610 0.01717 0.00802 -0.0835 0.9028 0.0708
-2.500 0.0955 0.01640 0.00740 -0.0847 0.8975 0.1055
-2.250 0.1225 0.01561 0.00705 -0.0849 0.8886 0.2049
-2.000 0.1507 0.01421 0.00688 -0.0855 0.8824 0.4984
-1.750 0.1670 0.01402 0.00735 -0.0817 0.8725 0.7061
-1.500 0.1941 0.01402 0.00730 -0.0804 0.8656 0.7667
-1.250 0.2154 0.01403 0.00724 -0.0782 0.8549 0.7997
-1.000 0.2396 0.01396 0.00709 -0.0766 0.8461 0.8271
-0.750 0.2620 0.01385 0.00692 -0.0745 0.8365 0.8551
-0.500 0.2807 0.01371 0.00675 -0.0716 0.8258 0.8857
-0.250 0.3050 0.01348 0.00647 -0.0698 0.8167 0.9160
0.000 0.3363 0.01331 0.00624 -0.0699 0.8060 0.9384
0.250 0.3720 0.01321 0.00604 -0.0712 0.7948 0.9559
0.500 0.4101 0.01310 0.00584 -0.0731 0.7838 0.9737
0.750 0.4452 0.01302 0.00565 -0.0744 0.7723 1.0000
1.000 0.4712 0.01306 0.00560 -0.0742 0.7586 1.0000
1.250 0.4983 0.01310 0.00556 -0.0741 0.7447 1.0000
1.500 0.5261 0.01314 0.00553 -0.0741 0.7302 1.0000
1.750 0.5541 0.01320 0.00550 -0.0740 0.7150 1.0000
2.000 0.5822 0.01326 0.00549 -0.0740 0.6989 1.0000
2.250 0.6102 0.01333 0.00547 -0.0739 0.6818 1.0000
2.500 0.6379 0.01343 0.00550 -0.0737 0.6634 1.0000
2.750 0.6650 0.01355 0.00555 -0.0735 0.6429 1.0000
3.000 0.6923 0.01369 0.00560 -0.0732 0.6217 1.0000
3.250 0.7191 0.01386 0.00568 -0.0729 0.5988 1.0000
3.500 0.7456 0.01406 0.00579 -0.0725 0.5749 1.0000
3.750 0.7717 0.01431 0.00594 -0.0721 0.5498 1.0000
4.000 0.7975 0.01459 0.00610 -0.0717 0.5247 1.0000
4.250 0.8229 0.01492 0.00634 -0.0712 0.4989 1.0000
4.500 0.8480 0.01527 0.00659 -0.0707 0.4731 1.0000
4.750 0.8727 0.01567 0.00687 -0.0701 0.4481 1.0000
5.000 0.8971 0.01609 0.00722 -0.0696 0.4234 1.0000
5.250 0.9212 0.01655 0.00759 -0.0691 0.3997 1.0000
5.500 0.9450 0.01703 0.00798 -0.0685 0.3768 1.0000
5.750 0.9687 0.01752 0.00842 -0.0679 0.3550 1.0000
6.000 0.9920 0.01804 0.00890 -0.0673 0.3336 1.0000
6.250 1.0148 0.01860 0.00939 -0.0666 0.3137 1.0000
6.500 1.0377 0.01914 0.00992 -0.0660 0.2937 1.0000
6.750 1.0601 0.01973 0.01050 -0.0653 0.2745 1.0000
7.000 1.0819 0.02035 0.01109 -0.0646 0.2560 1.0000
7.250 1.1031 0.02101 0.01171 -0.0638 0.2385 1.0000
7.500 1.1243 0.02167 0.01238 -0.0630 0.2211 1.0000
7.750 1.1449 0.02238 0.01311 -0.0622 0.2047 1.0000
8.000 1.1649 0.02312 0.01386 -0.0613 0.1891 1.0000
8.250 1.1842 0.02391 0.01466 -0.0603 0.1748 1.0000
8.500 1.2027 0.02475 0.01551 -0.0592 0.1613 1.0000
8.750 1.2203 0.02564 0.01642 -0.0581 0.1491 1.0000
9.000 1.2368 0.02659 0.01738 -0.0568 0.1380 1.0000
9.250 1.2537 0.02751 0.01840 -0.0556 0.1272 1.0000
9.500 1.2691 0.02854 0.01949 -0.0543 0.1181 1.0000
9.750 1.2816 0.02968 0.02061 -0.0527 0.1104 1.0000
10.000 1.2950 0.03073 0.02183 -0.0510 0.1027 1.0000
10.250 1.3042 0.03201 0.02310 -0.0490 0.0971 1.0000
10.500 1.3156 0.03322 0.02447 -0.0473 0.0910 1.0000
10.750 1.3230 0.03463 0.02591 -0.0454 0.0864 1.0000
11.000 1.3325 0.03607 0.02750 -0.0438 0.0817 1.0000
11.250 1.3404 0.03759 0.02916 -0.0422 0.0775 1.0000
11.500 1.3457 0.03933 0.03092 -0.0406 0.0744 1.0000
11.750 1.3531 0.04111 0.03287 -0.0393 0.0710 1.0000
12.000 1.3593 0.04296 0.03490 -0.0380 0.0677 1.0000
12.250 1.3637 0.04494 0.03699 -0.0369 0.0650 1.0000
12.500 1.3670 0.04715 0.03923 -0.0359 0.0629 1.0000
12.750 1.3712 0.04949 0.04180 -0.0350 0.0606 1.0000
13.000 1.3738 0.05200 0.04453 -0.0343 0.0583 1.0000
13.250 1.3749 0.05465 0.04737 -0.0338 0.0563 1.0000
13.500 1.3751 0.05742 0.05026 -0.0335 0.0545 1.0000
13.750 1.3752 0.06033 0.05325 -0.0334 0.0530 1.0000
14.000 1.3744 0.06360 0.05666 -0.0334 0.0517 1.0000
14.250 1.3688 0.06756 0.06092 -0.0339 0.0504 1.0000
14.500 1.3614 0.07186 0.06549 -0.0348 0.0492 1.0000
14.750 1.3526 0.07650 0.07037 -0.0362 0.0480 1.0000
15.000 1.3428 0.08147 0.07554 -0.0380 0.0470 1.0000
15.250 1.3323 0.08674 0.08100 -0.0402 0.0461 1.0000
15.500 1.3219 0.09223 0.08666 -0.0427 0.0453 1.0000
15.750 1.3118 0.09788 0.09246 -0.0454 0.0446 1.0000
16.000 1.3030 0.10347 0.09816 -0.0482 0.0439 1.0000
16.500 1.2730 0.11793 0.11294 -0.0564 0.0429 1.0000
16.750 1.2446 0.12885 0.12410 -0.0636 0.0429 1.0000
17.000 1.2086 0.14253 0.13797 -0.0728 0.0430 1.0000
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Polar data table (+)
Polar graphs
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