GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 200,000 Max Cl/Cd: 77.65 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe287-il-200000-n5.txt Download as CSV file: xf-goe287-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 287 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3407 0.09853 0.09539 -0.0127 0.9026 0.0228
-8.000 -0.3382 0.09569 0.09248 -0.0131 0.8678 0.0234
-7.750 -0.3350 0.09326 0.08998 -0.0164 0.8423 0.0260
-7.500 -0.3303 0.09015 0.08679 -0.0205 0.8242 0.0263
-7.250 -0.3184 0.08628 0.08284 -0.0262 0.8096 0.0265
-7.000 -0.3042 0.08208 0.07855 -0.0312 0.7967 0.0266
-6.750 -0.2898 0.07768 0.07407 -0.0350 0.7851 0.0266
-6.500 -0.2805 0.07354 0.06986 -0.0353 0.7742 0.0261
-6.250 -0.2701 0.06971 0.06597 -0.0359 0.7633 0.0246
-6.000 -0.2505 0.06518 0.06134 -0.0408 0.7523 0.0243
-5.500 -0.2049 0.05729 0.05320 -0.0496 0.7308 0.0296
-5.250 -0.1787 0.05262 0.04834 -0.0541 0.7205 0.0295
-5.000 -0.1502 0.04769 0.04315 -0.0585 0.7105 0.0292
-4.750 -0.1262 0.04580 0.04112 -0.0598 0.6998 0.0328
-4.500 -0.0966 0.04183 0.03686 -0.0628 0.6903 0.0339
-4.250 -0.0674 0.03779 0.03250 -0.0652 0.6810 0.0331
-4.000 -0.0372 0.03431 0.02864 -0.0669 0.6727 0.0343
-3.750 -0.0064 0.03105 0.02496 -0.0682 0.6644 0.0354
-3.500 0.0228 0.02825 0.02176 -0.0691 0.6574 0.0354
-3.250 0.0525 0.02595 0.01906 -0.0697 0.6503 0.0360
-3.000 0.0825 0.02448 0.01713 -0.0700 0.6442 0.0377
-2.750 0.1115 0.02301 0.01537 -0.0704 0.6379 0.0375
-2.500 0.1404 0.02141 0.01343 -0.0707 0.6325 0.0375
-2.250 0.1694 0.01985 0.01154 -0.0711 0.6274 0.0377
-2.000 0.1983 0.01851 0.00993 -0.0714 0.6214 0.0380
-1.750 0.2267 0.01742 0.00861 -0.0716 0.6159 0.0391
-1.500 0.2553 0.01677 0.00785 -0.0718 0.6093 0.0405
-1.250 0.2838 0.01614 0.00704 -0.0719 0.6029 0.0408
-1.000 0.3124 0.01554 0.00632 -0.0719 0.5971 0.0408
-0.750 0.3410 0.01503 0.00571 -0.0720 0.5912 0.0410
-0.500 0.3692 0.01462 0.00520 -0.0720 0.5860 0.0414
-0.250 0.3977 0.01424 0.00480 -0.0721 0.5804 0.0421
0.000 0.4261 0.01394 0.00446 -0.0723 0.5753 0.0430
0.250 0.4544 0.01372 0.00418 -0.0723 0.5710 0.0442
0.500 0.4831 0.01351 0.00398 -0.0725 0.5657 0.0456
0.750 0.5116 0.01338 0.00381 -0.0727 0.5608 0.0471
1.000 0.5400 0.01333 0.00369 -0.0728 0.5565 0.0501
1.250 0.5686 0.01321 0.00360 -0.0730 0.5515 0.0548
1.500 0.5972 0.01316 0.00355 -0.0732 0.5463 0.0595
1.750 0.6255 0.01312 0.00350 -0.0733 0.5411 0.0767
2.250 0.6764 0.01116 0.00358 -0.0724 0.5287 1.0000
2.500 0.7046 0.01128 0.00362 -0.0725 0.5226 1.0000
2.750 0.7329 0.01139 0.00370 -0.0727 0.5166 1.0000
3.000 0.7609 0.01153 0.00377 -0.0727 0.5111 1.0000
3.250 0.7892 0.01164 0.00390 -0.0729 0.5043 1.0000
3.500 0.8171 0.01177 0.00400 -0.0730 0.4975 1.0000
3.750 0.8452 0.01189 0.00415 -0.0731 0.4896 1.0000
4.000 0.8729 0.01203 0.00427 -0.0732 0.4811 1.0000
4.250 0.9008 0.01214 0.00443 -0.0733 0.4700 1.0000
4.500 0.9285 0.01227 0.00459 -0.0734 0.4555 1.0000
4.750 0.9558 0.01242 0.00473 -0.0734 0.4349 1.0000
5.000 0.9823 0.01265 0.00486 -0.0733 0.3981 1.0000
5.250 1.0070 0.01313 0.00511 -0.0731 0.3542 1.0000
5.500 1.0317 0.01367 0.00550 -0.0730 0.3288 1.0000
5.750 1.0568 0.01416 0.00593 -0.0728 0.3134 1.0000
6.250 1.1042 0.01541 0.00699 -0.0724 0.2710 1.0000
6.500 1.1280 0.01598 0.00750 -0.0721 0.2533 1.0000
6.750 1.1520 0.01649 0.00799 -0.0719 0.2386 1.0000
7.000 1.1750 0.01709 0.00856 -0.0716 0.2192 1.0000
7.250 1.1971 0.01778 0.00913 -0.0712 0.1796 1.0000
7.500 1.1989 0.02084 0.01117 -0.0689 0.0370 1.0000
7.750 1.2166 0.02193 0.01231 -0.0679 0.0269 1.0000
8.000 1.2340 0.02297 0.01349 -0.0667 0.0232 1.0000
8.250 1.2524 0.02381 0.01448 -0.0657 0.0210 1.0000
8.500 1.2686 0.02480 0.01565 -0.0645 0.0190 1.0000
8.750 1.2819 0.02597 0.01697 -0.0631 0.0177 1.0000
9.000 1.2905 0.02739 0.01855 -0.0611 0.0168 1.0000
9.250 1.2898 0.02924 0.02056 -0.0584 0.0159 1.0000
9.500 1.2894 0.03134 0.02280 -0.0563 0.0153 1.0000
9.750 1.2960 0.03305 0.02464 -0.0552 0.0146 1.0000
10.000 1.3001 0.03513 0.02684 -0.0542 0.0139 1.0000
10.250 1.3015 0.03759 0.02942 -0.0534 0.0135 1.0000
10.500 1.3021 0.04022 0.03219 -0.0527 0.0131 1.0000
10.750 1.3024 0.04294 0.03502 -0.0520 0.0127 1.0000
11.000 1.3027 0.04572 0.03789 -0.0514 0.0124 1.0000
11.250 1.3032 0.04849 0.04075 -0.0508 0.0121 1.0000
11.500 1.3041 0.05124 0.04358 -0.0502 0.0118 1.0000
11.750 1.3053 0.05394 0.04635 -0.0496 0.0115 1.0000
12.000 1.3066 0.05665 0.04912 -0.0491 0.0111 1.0000
12.250 1.3076 0.05933 0.05183 -0.0482 0.0107 1.0000
12.500 1.3108 0.06173 0.05426 -0.0468 0.0103 1.0000
12.750 1.3152 0.06424 0.05692 -0.0464 0.0100 1.0000
13.000 1.3197 0.06671 0.05953 -0.0457 0.0097 1.0000
13.250 1.3241 0.06923 0.06222 -0.0449 0.0095 1.0000
13.500 1.3279 0.07190 0.06503 -0.0442 0.0093 1.0000
13.750 1.3308 0.07476 0.06805 -0.0436 0.0091 1.0000
14.000 1.3323 0.07787 0.07133 -0.0432 0.0089 1.0000
14.250 1.3321 0.08127 0.07490 -0.0431 0.0088 1.0000
14.500 1.3303 0.08498 0.07879 -0.0433 0.0087 1.0000
14.750 1.3267 0.08902 0.08303 -0.0438 0.0086 1.0000
15.000 1.3214 0.09339 0.08759 -0.0446 0.0085 1.0000
15.250 1.3146 0.09809 0.09249 -0.0458 0.0085 1.0000
15.500 1.3066 0.10311 0.09770 -0.0474 0.0084 1.0000
15.750 1.2978 0.10841 0.10318 -0.0494 0.0083 1.0000
16.000 1.2884 0.11397 0.10893 -0.0518 0.0082 1.0000
16.250 1.2783 0.11983 0.11498 -0.0546 0.0082 1.0000
16.500 1.2681 0.12597 0.12129 -0.0578 0.0081 1.0000
16.750 1.2573 0.13254 0.12804 -0.0614 0.0081 1.0000
17.000 1.2467 0.13932 0.13499 -0.0655 0.0080 1.0000
17.250 1.2353 0.14665 0.14248 -0.0701 0.0080 1.0000
17.500 1.2222 0.15479 0.15081 -0.0753 0.0080 1.0000
17.750 1.2087 0.16352 0.15971 -0.0811 0.0080 1.0000
18.000 1.1933 0.17336 0.16973 -0.0877 0.0081 1.0000
18.250 1.1752 0.18488 0.18142 -0.0954 0.0084 1.0000
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Polar data table (+)
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