GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 624 AIRFOIL (goe624-il) Reynolds number: 200,000 Max Cl/Cd: 69.85 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe624-il-200000-n5.txt Download as CSV file: xf-goe624-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 624 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4982 0.04859 0.04420 -0.1040 0.9248 0.0358
-11.000 -0.5397 0.04148 0.03655 -0.1071 0.9050 0.0358
-10.750 -0.5531 0.03710 0.03160 -0.1069 0.8920 0.0361
-10.500 -0.5457 0.03483 0.02905 -0.1062 0.8827 0.0364
-10.250 -0.5312 0.03333 0.02741 -0.1055 0.8740 0.0367
-10.000 -0.5157 0.03184 0.02575 -0.1048 0.8661 0.0371
-9.750 -0.4988 0.03042 0.02414 -0.1041 0.8579 0.0374
-9.250 -0.4613 0.02777 0.02108 -0.1029 0.8434 0.0382
-9.000 -0.4410 0.02655 0.01964 -0.1022 0.8362 0.0387
-8.750 -0.4196 0.02541 0.01827 -0.1016 0.8293 0.0392
-8.500 -0.3973 0.02435 0.01700 -0.1011 0.8218 0.0398
-8.250 -0.3743 0.02339 0.01580 -0.1005 0.8156 0.0405
-8.000 -0.3503 0.02252 0.01475 -0.1001 0.8085 0.0412
-7.750 -0.3260 0.02182 0.01402 -0.0997 0.8011 0.0418
-7.500 -0.3012 0.02119 0.01330 -0.0993 0.7940 0.0425
-7.250 -0.2762 0.02056 0.01258 -0.0989 0.7845 0.0432
-7.000 -0.2511 0.01994 0.01182 -0.0984 0.7758 0.0440
-6.750 -0.2256 0.01934 0.01111 -0.0980 0.7659 0.0449
-6.500 -0.1997 0.01878 0.01040 -0.0976 0.7586 0.0458
-6.250 -0.1736 0.01826 0.00983 -0.0974 0.7504 0.0468
-6.000 -0.1472 0.01783 0.00935 -0.0971 0.7434 0.0480
-5.750 -0.1204 0.01745 0.00891 -0.0969 0.7362 0.0497
-5.500 -0.0935 0.01706 0.00843 -0.0967 0.7287 0.0518
-5.250 -0.0667 0.01671 0.00804 -0.0965 0.7220 0.0539
-5.000 -0.0395 0.01638 0.00769 -0.0963 0.7141 0.0566
-4.750 -0.0123 0.01607 0.00731 -0.0961 0.7073 0.0599
-4.500 0.0152 0.01580 0.00701 -0.0960 0.7003 0.0645
-4.250 0.0427 0.01557 0.00675 -0.0959 0.6930 0.0700
-4.000 0.0704 0.01537 0.00650 -0.0958 0.6863 0.0769
-3.750 0.0981 0.01520 0.00629 -0.0957 0.6785 0.0842
-3.500 0.1258 0.01505 0.00608 -0.0956 0.6717 0.0912
-3.250 0.1536 0.01487 0.00589 -0.0956 0.6647 0.0973
-3.000 0.1814 0.01474 0.00571 -0.0955 0.6577 0.1038
-2.750 0.2090 0.01460 0.00552 -0.0954 0.6513 0.1103
-2.500 0.2368 0.01448 0.00539 -0.0954 0.6435 0.1185
-2.250 0.2643 0.01434 0.00525 -0.0953 0.6365 0.1292
-2.000 0.2919 0.01421 0.00514 -0.0952 0.6291 0.1408
-1.750 0.3195 0.01409 0.00502 -0.0952 0.6218 0.1528
-1.500 0.3471 0.01398 0.00491 -0.0951 0.6153 0.1676
-1.250 0.3746 0.01384 0.00485 -0.0951 0.6077 0.1896
-1.000 0.4019 0.01372 0.00477 -0.0950 0.6005 0.2198
-0.750 0.4291 0.01358 0.00474 -0.0949 0.5928 0.2571
-0.500 0.4559 0.01342 0.00471 -0.0948 0.5848 0.3060
-0.250 0.4823 0.01323 0.00470 -0.0947 0.5774 0.3732
0.000 0.5079 0.01295 0.00473 -0.0943 0.5696 0.4670
0.250 0.5318 0.01261 0.00478 -0.0935 0.5627 0.5952
0.500 0.5531 0.01225 0.00492 -0.0918 0.5546 0.7451
0.750 0.5797 0.01213 0.00502 -0.0907 0.5469 0.8780
1.000 0.6222 0.01219 0.00508 -0.0934 0.5377 0.9555
1.250 0.6725 0.01233 0.00509 -0.0982 0.5293 1.0000
1.500 0.6966 0.01245 0.00514 -0.0975 0.5215 1.0000
1.750 0.7207 0.01260 0.00518 -0.0968 0.5141 1.0000
2.000 0.7452 0.01276 0.00526 -0.0962 0.5067 1.0000
2.250 0.7698 0.01292 0.00534 -0.0957 0.4995 1.0000
2.500 0.7945 0.01311 0.00542 -0.0951 0.4935 1.0000
2.750 0.8196 0.01328 0.00555 -0.0947 0.4868 1.0000
3.000 0.8444 0.01349 0.00567 -0.0942 0.4807 1.0000
3.250 0.8695 0.01369 0.00581 -0.0938 0.4750 1.0000
3.500 0.8947 0.01389 0.00598 -0.0934 0.4693 1.0000
3.750 0.9197 0.01412 0.00613 -0.0929 0.4639 1.0000
4.000 0.9448 0.01436 0.00631 -0.0925 0.4590 1.0000
4.250 0.9700 0.01458 0.00652 -0.0922 0.4537 1.0000
4.500 0.9949 0.01482 0.00672 -0.0918 0.4487 1.0000
4.750 1.0197 0.01510 0.00692 -0.0914 0.4440 1.0000
5.000 1.0443 0.01533 0.00717 -0.0910 0.4382 1.0000
5.250 1.0680 0.01559 0.00740 -0.0904 0.4314 1.0000
5.500 1.0914 0.01589 0.00763 -0.0898 0.4250 1.0000
5.750 1.1149 0.01614 0.00791 -0.0892 0.4184 1.0000
6.000 1.1384 0.01643 0.00817 -0.0886 0.4133 1.0000
6.250 1.1621 0.01675 0.00844 -0.0881 0.4092 1.0000
6.500 1.1858 0.01702 0.00877 -0.0876 0.4048 1.0000
6.750 1.2089 0.01731 0.00910 -0.0870 0.4002 1.0000
7.000 1.2315 0.01763 0.00942 -0.0863 0.3955 1.0000
7.250 1.2539 0.01798 0.00973 -0.0856 0.3912 1.0000
7.500 1.2755 0.01828 0.01012 -0.0848 0.3861 1.0000
7.750 1.2965 0.01862 0.01050 -0.0839 0.3810 1.0000
8.000 1.3170 0.01899 0.01085 -0.0830 0.3765 1.0000
8.250 1.3373 0.01935 0.01126 -0.0820 0.3720 1.0000
8.500 1.3555 0.01971 0.01170 -0.0806 0.3669 1.0000
8.750 1.3724 0.02011 0.01214 -0.0791 0.3620 1.0000
9.000 1.3894 0.02057 0.01257 -0.0777 0.3575 1.0000
9.250 1.4057 0.02102 0.01314 -0.0762 0.3516 1.0000
9.500 1.4204 0.02154 0.01370 -0.0745 0.3452 1.0000
9.750 1.4347 0.02212 0.01431 -0.0729 0.3390 1.0000
10.000 1.4483 0.02275 0.01501 -0.0713 0.3315 1.0000
10.250 1.4605 0.02347 0.01573 -0.0696 0.3249 1.0000
10.500 1.4738 0.02421 0.01656 -0.0682 0.3172 1.0000
10.750 1.4843 0.02509 0.01745 -0.0665 0.3099 1.0000
11.000 1.4964 0.02598 0.01842 -0.0652 0.3021 1.0000
11.250 1.5055 0.02705 0.01950 -0.0636 0.2947 1.0000
11.500 1.5159 0.02812 0.02064 -0.0622 0.2866 1.0000
11.750 1.5222 0.02946 0.02197 -0.0606 0.2787 1.0000
12.000 1.5304 0.03077 0.02335 -0.0593 0.2700 1.0000
12.250 1.5353 0.03234 0.02491 -0.0578 0.2624 1.0000
12.500 1.5422 0.03384 0.02649 -0.0566 0.2547 1.0000
12.750 1.5453 0.03564 0.02829 -0.0552 0.2477 1.0000
13.000 1.5507 0.03736 0.03007 -0.0541 0.2402 1.0000
13.250 1.5523 0.03939 0.03211 -0.0529 0.2339 1.0000
13.500 1.5575 0.04121 0.03402 -0.0519 0.2278 1.0000
13.750 1.5600 0.04331 0.03616 -0.0509 0.2220 1.0000
14.000 1.5624 0.04548 0.03837 -0.0501 0.2171 1.0000
14.250 1.5661 0.04761 0.04058 -0.0494 0.2117 1.0000
14.500 1.5665 0.05007 0.04308 -0.0486 0.2064 1.0000
14.750 1.5680 0.05251 0.04559 -0.0481 0.2013 1.0000
15.000 1.5688 0.05510 0.04826 -0.0476 0.1956 1.0000
15.250 1.5662 0.05804 0.05121 -0.0471 0.1904 1.0000
15.500 1.5668 0.06076 0.05403 -0.0468 0.1851 1.0000
15.750 1.5649 0.06379 0.05712 -0.0466 0.1796 1.0000
16.000 1.5609 0.06707 0.06041 -0.0464 0.1745 1.0000
16.250 1.5596 0.07019 0.06366 -0.0465 0.1690 1.0000
16.500 1.5548 0.07372 0.06724 -0.0466 0.1636 1.0000
16.750 1.5511 0.07716 0.07075 -0.0467 0.1588 1.0000
17.000 1.5478 0.08067 0.07436 -0.0470 0.1533 1.0000
17.250 1.5412 0.08458 0.07830 -0.0474 0.1482 1.0000
17.500 1.5373 0.08825 0.08209 -0.0479 0.1428 1.0000
17.750 1.5303 0.09237 0.08627 -0.0486 0.1371 1.0000
18.000 1.5241 0.09642 0.09039 -0.0493 0.1316 1.0000
18.250 1.5169 0.10067 0.09472 -0.0502 0.1254 1.0000
18.500 1.5090 0.10505 0.09915 -0.0512 0.1196 1.0000
18.750 1.5003 0.10959 0.10375 -0.0524 0.1133 1.0000
19.000 1.4919 0.11411 0.10831 -0.0536 0.1079 1.0000
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Polar data table (+)
Polar graphs
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