GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 200,000 Max Cl/Cd: 75.14 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe389-il-200000.txt Download as CSV file: xf-goe389-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 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 -0.3652 0.08801 0.08476 -0.0361 1.0000 0.0574
-7.750 -0.3849 0.08586 0.08272 -0.0380 1.0000 0.0579
-7.500 -0.4019 0.08319 0.08011 -0.0400 1.0000 0.0582
-7.250 -0.4148 0.08032 0.07724 -0.0409 1.0000 0.0583
-7.000 -0.4148 0.07505 0.07204 -0.0393 0.9986 0.0594
-6.750 -0.3915 0.07263 0.06963 -0.0381 0.9956 0.0610
-6.500 -0.3614 0.06875 0.06571 -0.0431 0.9904 0.0639
-6.250 -0.3161 0.05638 0.05278 -0.0665 0.9800 0.0722
-6.000 -0.2903 0.05423 0.05080 -0.0664 0.9755 0.0743
-5.750 -0.2551 0.05091 0.04740 -0.0709 0.9716 0.0784
-5.500 -0.2200 0.04358 0.03953 -0.0800 0.9621 0.0874
-5.250 -0.1838 0.04109 0.03706 -0.0831 0.9587 0.0911
-5.000 -0.1505 0.03722 0.03284 -0.0873 0.9507 0.1028
-4.750 -0.1124 0.03434 0.02961 -0.0914 0.9462 0.1160
-4.500 -0.0723 0.02485 0.01884 -0.0937 0.9413 0.0676
-4.250 -0.0393 0.02244 0.01601 -0.0948 0.9343 0.0666
-4.000 -0.0018 0.02011 0.01325 -0.0965 0.9301 0.0645
-3.750 0.0290 0.01868 0.01153 -0.0968 0.9216 0.0642
-3.500 0.0639 0.01747 0.01009 -0.0979 0.9158 0.0649
-3.250 0.0932 0.01673 0.00922 -0.0978 0.9066 0.0672
-3.000 0.1258 0.01588 0.00824 -0.0983 0.8998 0.0688
-2.750 0.1527 0.01524 0.00750 -0.0977 0.8891 0.0701
-2.500 0.1808 0.01462 0.00681 -0.0973 0.8798 0.0717
-2.250 0.2080 0.01374 0.00597 -0.0970 0.8707 0.0754
-2.000 0.2339 0.01329 0.00553 -0.0963 0.8595 0.0806
-1.750 0.2604 0.01279 0.00503 -0.0958 0.8489 0.0900
-1.500 0.2876 0.01218 0.00451 -0.0953 0.8391 0.1179
-1.250 0.3112 0.01109 0.00433 -0.0948 0.8272 0.3508
-1.000 0.3333 0.01030 0.00427 -0.0935 0.8150 0.5710
-0.750 0.3768 0.00922 0.00412 -0.0953 0.8034 1.0000
-0.500 0.4028 0.00924 0.00395 -0.0946 0.7900 1.0000
-0.250 0.4289 0.00927 0.00380 -0.0939 0.7756 1.0000
0.000 0.4549 0.00933 0.00368 -0.0932 0.7602 1.0000
0.250 0.4809 0.00941 0.00360 -0.0925 0.7437 1.0000
0.500 0.5067 0.00952 0.00355 -0.0918 0.7262 1.0000
0.750 0.5324 0.00966 0.00351 -0.0911 0.7077 1.0000
1.000 0.5579 0.00979 0.00351 -0.0904 0.6873 1.0000
1.250 0.5832 0.00992 0.00351 -0.0897 0.6646 1.0000
1.500 0.6085 0.01006 0.00351 -0.0890 0.6413 1.0000
1.750 0.6338 0.01020 0.00350 -0.0883 0.6177 1.0000
2.000 0.6591 0.01037 0.00353 -0.0877 0.5951 1.0000
2.250 0.6843 0.01059 0.00358 -0.0871 0.5748 1.0000
2.500 0.7097 0.01085 0.00367 -0.0865 0.5571 1.0000
2.750 0.7351 0.01114 0.00380 -0.0860 0.5413 1.0000
3.000 0.7608 0.01143 0.00398 -0.0855 0.5272 1.0000
3.250 0.7868 0.01171 0.00419 -0.0852 0.5147 1.0000
3.500 0.8130 0.01200 0.00443 -0.0849 0.5045 1.0000
3.750 0.8393 0.01234 0.00467 -0.0846 0.4955 1.0000
4.000 0.8655 0.01261 0.00495 -0.0843 0.4861 1.0000
4.250 0.8918 0.01293 0.00523 -0.0841 0.4780 1.0000
4.500 0.9181 0.01323 0.00551 -0.0838 0.4697 1.0000
4.750 0.9442 0.01354 0.00583 -0.0836 0.4615 1.0000
5.000 0.9703 0.01385 0.00613 -0.0833 0.4537 1.0000
5.250 0.9962 0.01415 0.00647 -0.0830 0.4458 1.0000
5.500 1.0221 0.01446 0.00676 -0.0827 0.4378 1.0000
5.750 1.0473 0.01472 0.00711 -0.0822 0.4286 1.0000
6.000 1.0713 0.01494 0.00733 -0.0816 0.4160 1.0000
6.250 1.0946 0.01512 0.00753 -0.0808 0.4022 1.0000
6.500 1.1185 0.01536 0.00777 -0.0801 0.3907 1.0000
6.750 1.1418 0.01553 0.00801 -0.0793 0.3774 1.0000
7.000 1.1643 0.01571 0.00822 -0.0784 0.3618 1.0000
7.250 1.1873 0.01591 0.00850 -0.0776 0.3476 1.0000
7.500 1.2102 0.01615 0.00883 -0.0768 0.3327 1.0000
7.750 1.2323 0.01640 0.00914 -0.0759 0.3127 1.0000
8.000 1.2526 0.01678 0.00948 -0.0747 0.2847 1.0000
8.250 1.2704 0.01738 0.00994 -0.0733 0.2466 1.0000
8.500 1.2853 0.01829 0.01062 -0.0715 0.1985 1.0000
8.750 1.2943 0.01973 0.01170 -0.0690 0.1426 1.0000
9.000 1.3034 0.02115 0.01291 -0.0666 0.1116 1.0000
9.250 1.3109 0.02263 0.01413 -0.0639 0.0636 1.0000
9.500 1.3125 0.02427 0.01559 -0.0604 0.0415 1.0000
9.750 1.3188 0.02555 0.01689 -0.0575 0.0336 1.0000
10.000 1.3257 0.02683 0.01824 -0.0548 0.0305 1.0000
10.250 1.3328 0.02814 0.01966 -0.0525 0.0287 1.0000
10.500 1.3377 0.02967 0.02131 -0.0501 0.0273 1.0000
10.750 1.3399 0.03147 0.02323 -0.0478 0.0264 1.0000
11.000 1.3387 0.03367 0.02556 -0.0457 0.0256 1.0000
11.250 1.3368 0.03607 0.02808 -0.0438 0.0251 1.0000
11.500 1.3371 0.03842 0.03057 -0.0424 0.0245 1.0000
11.750 1.3367 0.04098 0.03326 -0.0413 0.0239 1.0000
12.000 1.3357 0.04371 0.03612 -0.0404 0.0234 1.0000
12.250 1.3340 0.04659 0.03910 -0.0396 0.0229 1.0000
12.500 1.3324 0.04954 0.04216 -0.0389 0.0225 1.0000
12.750 1.3311 0.05247 0.04520 -0.0382 0.0222 1.0000
13.000 1.3306 0.05535 0.04818 -0.0374 0.0220 1.0000
13.250 1.3312 0.05811 0.05102 -0.0366 0.0217 1.0000
13.500 1.3332 0.06072 0.05371 -0.0357 0.0215 1.0000
13.750 1.3367 0.06317 0.05625 -0.0347 0.0213 1.0000
14.000 1.3417 0.06553 0.05870 -0.0336 0.0212 1.0000
14.250 1.3469 0.06793 0.06122 -0.0325 0.0211 1.0000
14.500 1.3518 0.07051 0.06395 -0.0315 0.0211 1.0000
14.750 1.3549 0.07344 0.06705 -0.0307 0.0211 1.0000
15.000 1.3554 0.07680 0.07064 -0.0303 0.0213 1.0000
15.250 1.3528 0.08060 0.07467 -0.0302 0.0214 1.0000
15.500 1.3474 0.08485 0.07913 -0.0307 0.0214 1.0000
15.750 1.3397 0.08952 0.08402 -0.0316 0.0214 1.0000
16.000 1.3299 0.09463 0.08935 -0.0330 0.0215 1.0000
16.250 1.3171 0.10033 0.09528 -0.0351 0.0215 1.0000
16.500 1.3007 0.10693 0.10213 -0.0381 0.0217 1.0000
16.750 1.2793 0.11481 0.11031 -0.0422 0.0220 1.0000
17.000 1.2578 0.12307 0.11881 -0.0468 0.0223 1.0000
17.250 1.2345 0.13219 0.12817 -0.0524 0.0227 1.0000
17.500 1.2104 0.14205 0.13826 -0.0587 0.0231 1.0000
17.750 1.1853 0.15287 0.14925 -0.0659 0.0236 1.0000
18.000 1.1595 0.16470 0.16124 -0.0739 0.0242 1.0000
18.250 1.1362 0.17662 0.17325 -0.0815 0.0249 1.0000
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