SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 200,000 Max Cl/Cd: 76.57 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3002-il-200000.txt Download as CSV file: xf-s3002-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3684 0.09270 0.08920 -0.0401 1.0000 0.0438
-8.500 -0.3775 0.08914 0.08573 -0.0431 1.0000 0.0440
-8.250 -0.3887 0.08585 0.08253 -0.0448 1.0000 0.0440
-8.000 -0.3760 0.08205 0.07875 -0.0400 1.0000 0.0452
-7.750 -0.3733 0.08011 0.07686 -0.0378 1.0000 0.0461
-7.500 -0.3844 0.07825 0.07509 -0.0357 1.0000 0.0466
-7.250 -0.4026 0.07661 0.07355 -0.0332 1.0000 0.0468
-7.000 -0.4207 0.07465 0.07167 -0.0318 1.0000 0.0471
-6.750 -0.4353 0.07216 0.06922 -0.0316 1.0000 0.0474
-6.500 -0.4224 0.06766 0.06467 -0.0372 0.9967 0.0493
-6.000 -0.3623 0.05256 0.04905 -0.0595 0.9843 0.0567
-5.750 -0.3367 0.04975 0.04621 -0.0620 0.9785 0.0596
-5.500 -0.3007 0.04369 0.03958 -0.0700 0.9730 0.0684
-5.250 -0.2728 0.04165 0.03764 -0.0717 0.9683 0.0736
-5.000 -0.2401 0.03759 0.03317 -0.0759 0.9623 0.0831
-4.750 -0.1933 0.02748 0.02139 -0.0792 0.9592 0.0446
-4.500 -0.1584 0.02378 0.01744 -0.0812 0.9557 0.0409
-4.250 -0.1255 0.02128 0.01451 -0.0820 0.9498 0.0399
-4.000 -0.0856 0.01994 0.01284 -0.0841 0.9463 0.0429
-3.750 -0.0432 0.01851 0.01113 -0.0865 0.9440 0.0440
-3.500 -0.0106 0.01677 0.00941 -0.0874 0.9387 0.0470
-3.250 0.0246 0.01602 0.00864 -0.0887 0.9331 0.0524
-3.000 0.0631 0.01485 0.00749 -0.0906 0.9294 0.0580
-2.750 0.0950 0.01428 0.00691 -0.0912 0.9224 0.0670
-2.500 0.1288 0.01340 0.00614 -0.0923 0.9161 0.0873
-2.250 0.1609 0.01145 0.00549 -0.0941 0.9107 0.3853
-2.000 0.1816 0.01069 0.00575 -0.0920 0.9015 0.6663
-1.750 0.2091 0.01071 0.00580 -0.0909 0.8945 0.7398
-1.500 0.2309 0.01079 0.00590 -0.0884 0.8849 0.7887
-1.250 0.2521 0.01081 0.00592 -0.0859 0.8760 0.8238
-1.000 0.2740 0.01071 0.00579 -0.0835 0.8674 0.8459
-0.750 0.2946 0.01065 0.00569 -0.0812 0.8572 0.8660
-0.500 0.3180 0.01051 0.00547 -0.0793 0.8493 0.8840
-0.250 0.3366 0.01038 0.00533 -0.0767 0.8382 0.9019
0.000 0.3545 0.01021 0.00514 -0.0736 0.8280 0.9253
0.250 0.3801 0.00997 0.00485 -0.0721 0.8192 0.9503
0.500 0.4168 0.00984 0.00467 -0.0734 0.8077 0.9697
0.750 0.4579 0.00972 0.00448 -0.0759 0.7966 0.9830
1.000 0.4981 0.00962 0.00428 -0.0783 0.7851 0.9959
1.250 0.5236 0.00960 0.00418 -0.0779 0.7726 1.0000
1.500 0.5477 0.00962 0.00413 -0.0773 0.7583 1.0000
1.750 0.5745 0.00964 0.00409 -0.0772 0.7435 1.0000
2.000 0.6025 0.00967 0.00404 -0.0772 0.7280 1.0000
2.250 0.6309 0.00971 0.00400 -0.0773 0.7115 1.0000
2.500 0.6592 0.00978 0.00401 -0.0774 0.6931 1.0000
2.750 0.6873 0.00986 0.00402 -0.0774 0.6728 1.0000
3.000 0.7153 0.00997 0.00403 -0.0774 0.6519 1.0000
3.250 0.7429 0.01012 0.00408 -0.0773 0.6287 1.0000
3.500 0.7700 0.01030 0.00415 -0.0770 0.6044 1.0000
3.750 0.7966 0.01052 0.00426 -0.0768 0.5775 1.0000
4.000 0.8227 0.01078 0.00440 -0.0764 0.5497 1.0000
4.250 0.8484 0.01108 0.00459 -0.0760 0.5213 1.0000
4.500 0.8737 0.01143 0.00479 -0.0756 0.4931 1.0000
4.750 0.8986 0.01182 0.00503 -0.0751 0.4654 1.0000
5.000 0.9234 0.01221 0.00531 -0.0747 0.4382 1.0000
5.250 0.9479 0.01262 0.00564 -0.0742 0.4123 1.0000
5.500 0.9721 0.01308 0.00597 -0.0736 0.3880 1.0000
5.750 0.9962 0.01352 0.00633 -0.0731 0.3638 1.0000
6.000 1.0199 0.01400 0.00673 -0.0726 0.3413 1.0000
6.250 1.0435 0.01447 0.00714 -0.0720 0.3187 1.0000
6.500 1.0665 0.01501 0.00757 -0.0714 0.2978 1.0000
6.750 1.0898 0.01549 0.00804 -0.0708 0.2763 1.0000
7.000 1.1122 0.01605 0.00852 -0.0701 0.2564 1.0000
7.250 1.1342 0.01663 0.00904 -0.0693 0.2372 1.0000
7.500 1.1563 0.01720 0.00959 -0.0686 0.2184 1.0000
7.750 1.1777 0.01783 0.01019 -0.0678 0.2008 1.0000
8.000 1.1984 0.01851 0.01082 -0.0669 0.1844 1.0000
8.250 1.2183 0.01923 0.01150 -0.0659 0.1690 1.0000
8.500 1.2378 0.02000 0.01223 -0.0649 0.1546 1.0000
8.750 1.2568 0.02080 0.01303 -0.0638 0.1415 1.0000
9.000 1.2750 0.02163 0.01388 -0.0626 0.1295 1.0000
9.250 1.2921 0.02256 0.01480 -0.0613 0.1187 1.0000
9.500 1.3074 0.02363 0.01581 -0.0597 0.1097 1.0000
9.750 1.3238 0.02451 0.01677 -0.0583 0.1015 1.0000
10.000 1.3382 0.02565 0.01794 -0.0567 0.0946 1.0000
10.250 1.3511 0.02662 0.01894 -0.0548 0.0886 1.0000
10.500 1.3634 0.02795 0.02030 -0.0530 0.0836 1.0000
10.750 1.3759 0.02897 0.02143 -0.0511 0.0790 1.0000
11.000 1.3869 0.03038 0.02281 -0.0494 0.0748 1.0000
11.250 1.3992 0.03174 0.02432 -0.0478 0.0714 1.0000
11.500 1.4102 0.03298 0.02569 -0.0461 0.0681 1.0000
11.750 1.4203 0.03433 0.02708 -0.0445 0.0652 1.0000
12.000 1.4337 0.03637 0.02913 -0.0434 0.0620 1.0000
12.250 1.4409 0.03783 0.03082 -0.0416 0.0599 1.0000
12.500 1.4484 0.03947 0.03264 -0.0401 0.0576 1.0000
12.750 1.4559 0.04111 0.03437 -0.0387 0.0554 1.0000
13.000 1.4662 0.04320 0.03645 -0.0378 0.0531 1.0000
13.250 1.4706 0.04573 0.03920 -0.0365 0.0514 1.0000
13.500 1.4713 0.04800 0.04172 -0.0351 0.0500 1.0000
13.750 1.4716 0.05049 0.04442 -0.0341 0.0486 1.0000
14.000 1.4711 0.05306 0.04716 -0.0332 0.0471 1.0000
14.250 1.4720 0.05554 0.04975 -0.0327 0.0457 1.0000
14.500 1.4754 0.05816 0.05240 -0.0323 0.0442 1.0000
14.750 1.4709 0.06270 0.05714 -0.0320 0.0429 1.0000
15.000 1.4594 0.06666 0.06137 -0.0323 0.0424 1.0000
15.250 1.4460 0.07120 0.06619 -0.0332 0.0419 1.0000
15.500 1.4310 0.07632 0.07157 -0.0346 0.0414 1.0000
15.750 1.4139 0.08207 0.07757 -0.0367 0.0409 1.0000
16.000 1.3949 0.08854 0.08428 -0.0396 0.0405 1.0000
16.250 1.3732 0.09592 0.09191 -0.0435 0.0403 1.0000
16.500 1.3476 0.10459 0.10083 -0.0485 0.0402 1.0000
16.750 1.3157 0.11523 0.11170 -0.0552 0.0405 1.0000
17.000 1.2754 0.12868 0.12539 -0.0643 0.0413 1.0000
17.250 1.2235 0.14633 0.14324 -0.0764 0.0424 1.0000
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Polar data table (+)
Polar graphs
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