S3025 9.38% (s3025-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 50,000 Max Cl/Cd: 39.17 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3025-il-50000-n5.txt Download as CSV file: xf-s3025-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3025 9.38%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3511 0.11013 0.10322 -0.0303 1.0000 0.1078
-8.750 -0.3632 0.10886 0.10210 -0.0330 1.0000 0.1094
-8.500 -0.3738 0.10706 0.10045 -0.0349 1.0000 0.1098
-8.250 -0.3544 0.10160 0.09500 -0.0329 1.0000 0.1112
-8.000 -0.3494 0.09825 0.09170 -0.0324 1.0000 0.1123
-7.750 -0.3499 0.09544 0.08900 -0.0322 1.0000 0.1128
-7.500 -0.3539 0.09288 0.08655 -0.0320 1.0000 0.1130
-7.000 -0.3629 0.08234 0.07611 -0.0376 1.0000 0.0534
-6.750 -0.3637 0.07925 0.07311 -0.0373 1.0000 0.0515
-6.500 -0.3660 0.07606 0.07000 -0.0377 1.0000 0.0498
-6.250 -0.3689 0.07250 0.06649 -0.0386 1.0000 0.0479
-5.750 -0.3699 0.06279 0.05650 -0.0437 1.0000 0.0425
-5.500 -0.3667 0.05994 0.05363 -0.0429 1.0000 0.0420
-5.250 -0.3619 0.05674 0.05034 -0.0426 1.0000 0.0414
-5.000 -0.3497 0.05308 0.04650 -0.0438 0.9984 0.0408
-4.750 -0.3159 0.04800 0.04099 -0.0492 0.9899 0.0401
-4.500 -0.2812 0.04332 0.03577 -0.0537 0.9818 0.0396
-4.250 -0.2452 0.03932 0.03115 -0.0574 0.9740 0.0398
-4.000 -0.2104 0.03601 0.02712 -0.0599 0.9654 0.0416
-3.750 -0.1724 0.03312 0.02358 -0.0625 0.9587 0.0436
-3.500 -0.1404 0.03094 0.02108 -0.0638 0.9496 0.0457
-3.250 -0.1044 0.02905 0.01879 -0.0654 0.9422 0.0479
-3.000 -0.0697 0.02745 0.01685 -0.0664 0.9339 0.0515
-2.750 -0.0357 0.02619 0.01538 -0.0674 0.9256 0.0590
-2.500 0.0014 0.02502 0.01400 -0.0690 0.9183 0.0712
-2.250 0.0345 0.02396 0.01293 -0.0700 0.9091 0.1019
-2.000 0.0727 0.02216 0.01201 -0.0726 0.9030 0.2597
-1.750 0.0958 0.02066 0.01179 -0.0717 0.8935 0.5400
-1.500 0.1538 0.01950 0.01121 -0.0754 0.8896 1.0000
-1.250 0.1853 0.01961 0.01083 -0.0762 0.8788 1.0000
-1.000 0.2195 0.01969 0.01052 -0.0774 0.8695 1.0000
-0.750 0.2535 0.01978 0.01026 -0.0785 0.8602 1.0000
-0.500 0.2824 0.01993 0.01012 -0.0787 0.8492 1.0000
-0.250 0.3137 0.02006 0.00999 -0.0793 0.8396 1.0000
0.000 0.3464 0.02015 0.00985 -0.0801 0.8304 1.0000
0.250 0.3734 0.02035 0.00986 -0.0799 0.8192 1.0000
0.500 0.4025 0.02053 0.00987 -0.0800 0.8090 1.0000
0.750 0.4353 0.02060 0.00979 -0.0807 0.8003 1.0000
1.000 0.4607 0.02086 0.00992 -0.0802 0.7886 1.0000
1.250 0.4874 0.02108 0.01004 -0.0799 0.7775 1.0000
1.500 0.5166 0.02123 0.01009 -0.0799 0.7675 1.0000
1.750 0.5452 0.02138 0.01017 -0.0797 0.7571 1.0000
2.000 0.5701 0.02165 0.01040 -0.0791 0.7450 1.0000
2.250 0.5960 0.02189 0.01060 -0.0785 0.7334 1.0000
2.500 0.6232 0.02208 0.01075 -0.0781 0.7223 1.0000
2.750 0.6524 0.02218 0.01084 -0.0779 0.7119 1.0000
3.000 0.6764 0.02247 0.01113 -0.0770 0.6990 1.0000
3.250 0.7009 0.02274 0.01141 -0.0762 0.6862 1.0000
3.500 0.7257 0.02299 0.01169 -0.0754 0.6734 1.0000
3.750 0.7508 0.02323 0.01200 -0.0747 0.6605 1.0000
4.000 0.7760 0.02346 0.01226 -0.0739 0.6475 1.0000
4.250 0.8011 0.02368 0.01253 -0.0731 0.6341 1.0000
4.500 0.8259 0.02391 0.01282 -0.0722 0.6203 1.0000
4.750 0.8503 0.02415 0.01317 -0.0712 0.6060 1.0000
5.000 0.8740 0.02440 0.01351 -0.0702 0.5910 1.0000
5.250 0.8973 0.02467 0.01387 -0.0691 0.5753 1.0000
5.500 0.9204 0.02495 0.01428 -0.0680 0.5591 1.0000
5.750 0.9434 0.02521 0.01464 -0.0668 0.5422 1.0000
6.000 0.9667 0.02544 0.01497 -0.0656 0.5248 1.0000
6.250 0.9894 0.02569 0.01530 -0.0644 0.5068 1.0000
6.500 1.0094 0.02611 0.01589 -0.0629 0.4866 1.0000
6.750 1.0309 0.02643 0.01630 -0.0615 0.4669 1.0000
7.000 1.0509 0.02686 0.01683 -0.0600 0.4461 1.0000
7.250 1.0704 0.02733 0.01738 -0.0584 0.4245 1.0000
7.500 1.0889 0.02788 0.01802 -0.0568 0.4026 1.0000
7.750 1.1067 0.02848 0.01872 -0.0551 0.3803 1.0000
8.000 1.1228 0.02921 0.01954 -0.0533 0.3575 1.0000
8.250 1.1387 0.02996 0.02031 -0.0515 0.3355 1.0000
8.500 1.1522 0.03091 0.02136 -0.0495 0.3129 1.0000
8.750 1.1653 0.03187 0.02233 -0.0475 0.2918 1.0000
9.000 1.1761 0.03302 0.02360 -0.0454 0.2704 1.0000
9.250 1.1857 0.03419 0.02483 -0.0432 0.2505 1.0000
9.500 1.1928 0.03553 0.02627 -0.0408 0.2307 1.0000
9.750 1.1968 0.03693 0.02774 -0.0382 0.2122 1.0000
10.000 1.1991 0.03848 0.02930 -0.0356 0.1949 1.0000
10.250 1.1998 0.04028 0.03116 -0.0333 0.1773 1.0000
10.500 1.1972 0.04232 0.03327 -0.0311 0.1595 1.0000
10.750 1.1915 0.04469 0.03562 -0.0294 0.1421 1.0000
11.000 1.1849 0.04742 0.03831 -0.0283 0.1255 1.0000
11.250 1.1791 0.05045 0.04140 -0.0276 0.1089 1.0000
11.500 1.1732 0.05374 0.04473 -0.0272 0.0951 1.0000
11.750 1.1672 0.05731 0.04837 -0.0270 0.0839 1.0000
12.000 1.1606 0.06108 0.05209 -0.0271 0.0759 1.0000
12.250 1.1560 0.06489 0.05606 -0.0272 0.0676 1.0000
12.500 1.1507 0.06887 0.06011 -0.0275 0.0616 1.0000
12.750 1.1463 0.07286 0.06422 -0.0280 0.0566 1.0000
13.000 1.1421 0.07682 0.06818 -0.0285 0.0534 1.0000
13.250 1.1408 0.08082 0.07248 -0.0288 0.0502 1.0000
13.500 1.1384 0.08498 0.07685 -0.0294 0.0478 1.0000
13.750 1.1357 0.08918 0.08119 -0.0302 0.0460 1.0000
14.000 1.1341 0.09320 0.08529 -0.0309 0.0444 1.0000
14.250 1.1306 0.09789 0.09014 -0.0321 0.0433 1.0000
14.500 1.1207 0.10407 0.09663 -0.0346 0.0426 1.0000
14.750 1.1084 0.11089 0.10373 -0.0378 0.0423 1.0000
15.000 1.0933 0.11870 0.11178 -0.0419 0.0420 1.0000
15.250 1.0760 0.12750 0.12079 -0.0469 0.0422 1.0000
15.500 1.0571 0.13731 0.13076 -0.0527 0.0425 1.0000
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Polar data table (+)
Polar graphs
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