GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 200,000 Max Cl/Cd: 65.15 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe285-il-200000.txt Download as CSV file: xf-goe285-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3529 0.08797 0.08435 -0.0340 1.0000 0.0732
-8.000 -0.3616 0.08525 0.08170 -0.0342 1.0000 0.0748
-7.750 -0.3868 0.08293 0.07950 -0.0338 1.0000 0.0761
-7.500 -0.4381 0.07910 0.07568 -0.0386 1.0000 0.0776
-7.250 -0.4694 0.07593 0.07234 -0.0385 1.0000 0.0779
-7.000 -0.4491 0.07150 0.06810 -0.0374 0.9983 0.0787
-6.750 -0.4223 0.06907 0.06572 -0.0379 0.9952 0.0798
-6.500 -0.3940 0.06584 0.06246 -0.0413 0.9906 0.0816
-6.250 -0.3625 0.06116 0.05766 -0.0480 0.9847 0.0847
-6.000 -0.3346 0.05235 0.04832 -0.0594 0.9750 0.0909
-5.750 -0.2996 0.04928 0.04526 -0.0627 0.9713 0.0923
-5.500 -0.2819 0.03476 0.02944 -0.0677 0.9610 0.0689
-5.250 -0.2446 0.03041 0.02472 -0.0709 0.9575 0.0645
-5.000 -0.2177 0.02515 0.01864 -0.0716 0.9487 0.0613
-4.750 -0.1771 0.02261 0.01566 -0.0742 0.9447 0.0614
-4.500 -0.1412 0.02117 0.01401 -0.0757 0.9382 0.0625
-4.250 -0.1056 0.02003 0.01269 -0.0771 0.9314 0.0646
-4.000 -0.0666 0.01878 0.01119 -0.0789 0.9271 0.0664
-3.750 -0.0371 0.01782 0.01005 -0.0788 0.9164 0.0679
-3.500 -0.0029 0.01671 0.00898 -0.0798 0.9093 0.0705
-3.250 0.0269 0.01606 0.00830 -0.0798 0.8985 0.0739
-3.000 0.0565 0.01543 0.00757 -0.0796 0.8878 0.0786
-2.750 0.0865 0.01481 0.00701 -0.0796 0.8773 0.0860
-2.500 0.1130 0.01421 0.00643 -0.0789 0.8634 0.0969
-2.250 0.1395 0.01381 0.00602 -0.0781 0.8489 0.1141
-2.000 0.1662 0.01357 0.00576 -0.0775 0.8346 0.1294
-1.750 0.1927 0.01332 0.00550 -0.0768 0.8206 0.1421
-1.500 0.2192 0.01307 0.00522 -0.0762 0.8068 0.1539
-1.250 0.2455 0.01285 0.00497 -0.0755 0.7925 0.1681
-1.000 0.2709 0.01259 0.00475 -0.0748 0.7768 0.1864
-0.750 0.2962 0.01227 0.00452 -0.0740 0.7611 0.2119
-0.500 0.3207 0.01174 0.00430 -0.0733 0.7463 0.2812
-0.250 0.3692 0.00985 0.00447 -0.0761 0.7316 0.9732
0.000 0.4250 0.00988 0.00427 -0.0817 0.7145 1.0000
0.250 0.4495 0.00994 0.00417 -0.0808 0.6986 1.0000
0.500 0.4740 0.01002 0.00408 -0.0799 0.6824 1.0000
0.750 0.4983 0.01011 0.00403 -0.0789 0.6658 1.0000
1.000 0.5226 0.01024 0.00399 -0.0780 0.6489 1.0000
1.250 0.5468 0.01038 0.00399 -0.0771 0.6317 1.0000
1.500 0.5708 0.01053 0.00401 -0.0761 0.6142 1.0000
1.750 0.5948 0.01069 0.00404 -0.0752 0.5964 1.0000
2.000 0.6187 0.01086 0.00410 -0.0742 0.5784 1.0000
2.250 0.6424 0.01104 0.00415 -0.0732 0.5603 1.0000
2.500 0.6661 0.01122 0.00422 -0.0723 0.5422 1.0000
2.750 0.6897 0.01141 0.00430 -0.0713 0.5241 1.0000
3.000 0.7131 0.01163 0.00439 -0.0703 0.5060 1.0000
3.250 0.7365 0.01188 0.00451 -0.0693 0.4883 1.0000
3.500 0.7599 0.01215 0.00466 -0.0684 0.4709 1.0000
3.750 0.7832 0.01246 0.00485 -0.0674 0.4542 1.0000
4.000 0.8066 0.01281 0.00507 -0.0665 0.4384 1.0000
4.250 0.8301 0.01316 0.00533 -0.0657 0.4229 1.0000
4.500 0.8538 0.01351 0.00562 -0.0649 0.4082 1.0000
4.750 0.8777 0.01387 0.00592 -0.0641 0.3949 1.0000
5.000 0.9017 0.01427 0.00624 -0.0634 0.3836 1.0000
5.250 0.9259 0.01464 0.00655 -0.0627 0.3734 1.0000
5.500 0.9502 0.01497 0.00687 -0.0621 0.3633 1.0000
5.750 0.9743 0.01536 0.00716 -0.0614 0.3547 1.0000
6.000 0.9984 0.01561 0.00748 -0.0608 0.3456 1.0000
6.250 1.0225 0.01599 0.00777 -0.0601 0.3381 1.0000
6.500 1.0465 0.01624 0.00809 -0.0595 0.3301 1.0000
6.750 1.0704 0.01662 0.00839 -0.0588 0.3233 1.0000
7.000 1.0944 0.01690 0.00877 -0.0582 0.3166 1.0000
7.250 1.1181 0.01722 0.00909 -0.0575 0.3102 1.0000
7.500 1.1416 0.01758 0.00947 -0.0569 0.3038 1.0000
7.750 1.1649 0.01788 0.00983 -0.0561 0.2974 1.0000
8.000 1.1883 0.01830 0.01020 -0.0555 0.2919 1.0000
8.250 1.2113 0.01862 0.01064 -0.0547 0.2861 1.0000
8.500 1.2333 0.01894 0.01101 -0.0539 0.2793 1.0000
8.750 1.2550 0.01933 0.01144 -0.0530 0.2725 1.0000
9.000 1.2757 0.01963 0.01183 -0.0519 0.2646 1.0000
9.250 1.2953 0.02002 0.01226 -0.0507 0.2558 1.0000
9.500 1.3138 0.02038 0.01266 -0.0493 0.2461 1.0000
9.750 1.3323 0.02072 0.01313 -0.0479 0.2359 1.0000
10.000 1.3486 0.02113 0.01360 -0.0462 0.2237 1.0000
10.250 1.3633 0.02154 0.01410 -0.0442 0.2059 1.0000
10.500 1.3726 0.02214 0.01463 -0.0415 0.1597 1.0000
10.750 1.3602 0.02432 0.01628 -0.0365 0.1083 1.0000
11.000 1.3564 0.02628 0.01817 -0.0329 0.0881 1.0000
11.250 1.3566 0.02804 0.01992 -0.0301 0.0772 1.0000
11.500 1.3574 0.02984 0.02174 -0.0277 0.0712 1.0000
11.750 1.3598 0.03162 0.02359 -0.0258 0.0668 1.0000
12.250 1.3599 0.03593 0.02804 -0.0227 0.0615 1.0000
12.500 1.3606 0.03823 0.03043 -0.0216 0.0595 1.0000
12.750 1.3594 0.04082 0.03309 -0.0207 0.0579 1.0000
13.000 1.3557 0.04377 0.03610 -0.0200 0.0566 1.0000
13.250 1.3502 0.04699 0.03935 -0.0194 0.0553 1.0000
13.500 1.3510 0.04967 0.04217 -0.0191 0.0542 1.0000
13.750 1.3508 0.05249 0.04509 -0.0188 0.0530 1.0000
14.000 1.3503 0.05539 0.04807 -0.0186 0.0519 1.0000
14.250 1.3497 0.05829 0.05104 -0.0184 0.0508 1.0000
14.500 1.3497 0.06113 0.05392 -0.0182 0.0499 1.0000
14.750 1.3506 0.06377 0.05657 -0.0177 0.0490 1.0000
15.000 1.3555 0.06574 0.05851 -0.0165 0.0479 1.0000
15.250 1.3585 0.06839 0.06130 -0.0164 0.0472 1.0000
15.500 1.3614 0.07103 0.06406 -0.0163 0.0463 1.0000
15.750 1.3643 0.07369 0.06683 -0.0162 0.0454 1.0000
16.000 1.3680 0.07625 0.06946 -0.0161 0.0445 1.0000
16.250 1.3730 0.07862 0.07190 -0.0158 0.0437 1.0000
16.500 1.3792 0.08077 0.07410 -0.0153 0.0429 1.0000
16.750 1.3921 0.08191 0.07519 -0.0139 0.0419 1.0000
17.000 1.3983 0.08425 0.07762 -0.0130 0.0411 1.0000
17.250 1.3924 0.08837 0.08196 -0.0142 0.0407 1.0000
17.500 1.3865 0.09260 0.08639 -0.0155 0.0403 1.0000
17.750 1.3800 0.09698 0.09097 -0.0169 0.0398 1.0000
18.000 1.3729 0.10156 0.09574 -0.0185 0.0394 1.0000
18.250 1.3646 0.10645 0.10083 -0.0204 0.0391 1.0000
18.500 1.3544 0.11178 0.10636 -0.0228 0.0389 1.0000
18.750 1.3421 0.11760 0.11239 -0.0256 0.0387 1.0000
19.000 1.3269 0.12412 0.11912 -0.0291 0.0385 1.0000
19.250 1.3080 0.13164 0.12686 -0.0335 0.0385 1.0000
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Polar data table (+)
Polar graphs
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