GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 200,000 Max Cl/Cd: 80.96 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe400-il-200000.txt Download as CSV file: xf-goe400-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3871 0.10001 0.09659 -0.0015 1.0000 0.0410
-7.750 -0.3803 0.09726 0.09388 -0.0041 1.0000 0.0430
-7.500 -0.3745 0.09583 0.09251 -0.0122 1.0000 0.0443
-7.250 -0.3576 0.09285 0.08953 -0.0216 1.0000 0.0446
-7.000 -0.3514 0.08717 0.08388 -0.0210 1.0000 0.0453
-6.750 -0.3429 0.08341 0.08015 -0.0173 1.0000 0.0462
-6.500 -0.3306 0.08039 0.07714 -0.0177 1.0000 0.0474
-6.250 -0.3164 0.07749 0.07426 -0.0197 1.0000 0.0496
-6.000 -0.2986 0.07437 0.07115 -0.0241 1.0000 0.0532
-5.750 -0.2594 0.07025 0.06692 -0.0410 1.0000 0.0558
-5.500 -0.2575 0.06650 0.06326 -0.0371 1.0000 0.0566
-5.250 -0.2513 0.06408 0.06091 -0.0348 1.0000 0.0576
-5.000 -0.2469 0.06220 0.05908 -0.0335 0.9996 0.0589
-4.500 -0.1442 0.05243 0.04904 -0.0549 0.9817 0.0688
-4.250 -0.1064 0.04920 0.04577 -0.0594 0.9698 0.0721
-4.000 -0.0439 0.04434 0.04051 -0.0719 0.9541 0.0793
-3.750 -0.0197 0.04172 0.03793 -0.0724 0.9340 0.0814
-3.500 0.0102 0.03944 0.03555 -0.0742 0.9125 0.0854
-3.250 0.0551 0.03616 0.03172 -0.0796 0.8910 0.0916
-3.000 0.0754 0.03374 0.02925 -0.0790 0.8699 0.0928
-2.750 0.0986 0.03185 0.02723 -0.0788 0.8511 0.0945
-2.500 0.1248 0.03011 0.02529 -0.0790 0.8339 0.0979
-2.250 0.1713 0.02053 0.01426 -0.0827 0.8220 0.0671
-2.000 0.1985 0.01834 0.01166 -0.0825 0.8073 0.0664
-1.750 0.2261 0.01648 0.00933 -0.0823 0.7934 0.0666
-1.500 0.2533 0.01520 0.00776 -0.0819 0.7800 0.0682
-1.250 0.2800 0.01512 0.00762 -0.0814 0.7670 0.0716
-1.000 0.3073 0.01449 0.00677 -0.0809 0.7551 0.0750
-0.750 0.3348 0.01379 0.00579 -0.0803 0.7441 0.0789
-0.500 0.3620 0.01363 0.00563 -0.0800 0.7319 0.0845
-0.250 0.3895 0.01338 0.00529 -0.0795 0.7207 0.0952
0.000 0.4168 0.01331 0.00510 -0.0791 0.7103 0.1182
0.250 0.4436 0.01313 0.00494 -0.0788 0.6998 0.1368
0.500 0.4707 0.01303 0.00480 -0.0785 0.6888 0.1483
0.750 0.4978 0.01305 0.00477 -0.0781 0.6786 0.1591
1.000 0.5246 0.01306 0.00477 -0.0778 0.6688 0.1738
1.250 0.5517 0.01290 0.00467 -0.0775 0.6578 0.1811
1.500 0.5788 0.01282 0.00457 -0.0771 0.6476 0.1849
1.750 0.6059 0.01280 0.00448 -0.0767 0.6381 0.1892
2.000 0.6329 0.01266 0.00443 -0.0764 0.6269 0.1927
2.250 0.6598 0.01260 0.00440 -0.0760 0.6157 0.1972
2.500 0.6866 0.01258 0.00436 -0.0756 0.6041 0.2028
2.750 0.7133 0.01253 0.00432 -0.0751 0.5923 0.2105
3.000 0.7401 0.01248 0.00435 -0.0747 0.5793 0.2245
3.250 0.7661 0.01216 0.00444 -0.0743 0.5668 0.3623
3.500 0.7947 0.01115 0.00442 -0.0740 0.5542 1.0000
3.750 0.8214 0.01130 0.00449 -0.0736 0.5413 1.0000
4.000 0.8480 0.01145 0.00458 -0.0731 0.5282 1.0000
4.250 0.8745 0.01160 0.00468 -0.0727 0.5141 1.0000
4.500 0.9008 0.01176 0.00480 -0.0722 0.4997 1.0000
4.750 0.9272 0.01196 0.00498 -0.0718 0.4863 1.0000
5.000 0.9535 0.01217 0.00516 -0.0714 0.4732 1.0000
5.250 0.9797 0.01239 0.00538 -0.0710 0.4592 1.0000
5.500 1.0056 0.01262 0.00561 -0.0705 0.4442 1.0000
5.750 1.0314 0.01286 0.00588 -0.0701 0.4283 1.0000
6.000 1.0572 0.01312 0.00617 -0.0696 0.4125 1.0000
6.250 1.0827 0.01339 0.00648 -0.0691 0.3957 1.0000
6.500 1.1076 0.01368 0.00676 -0.0686 0.3739 1.0000
6.750 1.1319 0.01401 0.00707 -0.0680 0.3464 1.0000
7.000 1.1555 0.01443 0.00743 -0.0674 0.3152 1.0000
7.250 1.1786 0.01495 0.00786 -0.0668 0.2804 1.0000
7.500 1.2007 0.01564 0.00840 -0.0661 0.2372 1.0000
7.750 1.2211 0.01658 0.00914 -0.0653 0.1873 1.0000
8.000 1.2396 0.01782 0.01008 -0.0644 0.1360 1.0000
8.250 1.2545 0.01956 0.01144 -0.0632 0.0863 1.0000
8.500 1.2693 0.02133 0.01298 -0.0617 0.0512 1.0000
8.750 1.2855 0.02273 0.01435 -0.0603 0.0421 1.0000
9.000 1.3019 0.02401 0.01576 -0.0589 0.0377 1.0000
9.250 1.3154 0.02552 0.01732 -0.0574 0.0346 1.0000
9.500 1.3224 0.02767 0.01952 -0.0551 0.0327 1.0000
9.750 1.3355 0.02913 0.02112 -0.0533 0.0317 1.0000
10.000 1.3470 0.03076 0.02286 -0.0515 0.0306 1.0000
10.250 1.3579 0.03242 0.02463 -0.0496 0.0294 1.0000
10.500 1.3671 0.03406 0.02635 -0.0476 0.0281 1.0000
10.750 1.3753 0.03588 0.02824 -0.0457 0.0269 1.0000
11.000 1.3855 0.03828 0.03068 -0.0440 0.0259 1.0000
11.250 1.4021 0.04182 0.03436 -0.0428 0.0253 1.0000
11.500 1.4110 0.04442 0.03719 -0.0410 0.0250 1.0000
11.750 1.4160 0.04692 0.03994 -0.0392 0.0248 1.0000
12.000 1.4179 0.04975 0.04304 -0.0373 0.0247 1.0000
12.250 1.4163 0.05293 0.04648 -0.0356 0.0247 1.0000
12.500 1.4112 0.05641 0.05023 -0.0342 0.0247 1.0000
12.750 1.4028 0.06014 0.05423 -0.0333 0.0247 1.0000
13.000 1.3918 0.06420 0.05854 -0.0329 0.0246 1.0000
13.250 1.3786 0.06863 0.06322 -0.0332 0.0246 1.0000
13.500 1.3635 0.07349 0.06834 -0.0342 0.0246 1.0000
13.750 1.3469 0.07891 0.07399 -0.0357 0.0247 1.0000
14.000 1.3287 0.08473 0.08002 -0.0378 0.0247 1.0000
14.250 1.3092 0.09116 0.08662 -0.0405 0.0248 1.0000
14.500 1.2886 0.09832 0.09395 -0.0433 0.0250 1.0000
14.750 1.1329 0.09520 0.09099 -0.0280 0.0258 1.0000
15.000 1.1029 0.10159 0.09760 -0.0311 0.0261 1.0000
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Polar data table (+)
Polar graphs
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