GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 200,000 Max Cl/Cd: 58.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe647-il-200000-n5.txt Download as CSV file: xf-goe647-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5086 0.04903 0.04466 -0.0978 0.9761 0.0359
-11.250 -0.5293 0.04157 0.03673 -0.1080 0.9576 0.0360
-11.000 -0.5307 0.03731 0.03197 -0.1111 0.9439 0.0364
-10.750 -0.5078 0.03547 0.03005 -0.1128 0.9368 0.0369
-10.500 -0.4859 0.03394 0.02842 -0.1139 0.9278 0.0373
-10.250 -0.4633 0.03225 0.02657 -0.1151 0.9197 0.0379
-10.000 -0.4419 0.03061 0.02471 -0.1158 0.9101 0.0384
-9.750 -0.4201 0.02901 0.02289 -0.1163 0.9007 0.0389
-9.500 -0.3973 0.02751 0.02115 -0.1166 0.8912 0.0395
-9.250 -0.3758 0.02620 0.01960 -0.1163 0.8808 0.0400
-9.000 -0.3517 0.02497 0.01810 -0.1164 0.8713 0.0407
-8.750 -0.3307 0.02400 0.01686 -0.1156 0.8602 0.0414
-8.500 -0.3048 0.02306 0.01589 -0.1156 0.8510 0.0420
-8.250 -0.2828 0.02236 0.01513 -0.1147 0.8395 0.0426
-8.000 -0.2586 0.02163 0.01430 -0.1142 0.8296 0.0433
-7.750 -0.2354 0.02095 0.01351 -0.1134 0.8184 0.0439
-7.500 -0.2122 0.02030 0.01274 -0.1125 0.8077 0.0446
-7.250 -0.1881 0.01968 0.01198 -0.1118 0.7970 0.0454
-7.000 -0.1653 0.01913 0.01131 -0.1108 0.7854 0.0462
-6.750 -0.1414 0.01859 0.01065 -0.1100 0.7743 0.0472
-6.500 -0.1186 0.01810 0.01011 -0.1090 0.7606 0.0482
-6.250 -0.0958 0.01767 0.00961 -0.1079 0.7455 0.0494
-6.000 -0.0726 0.01727 0.00912 -0.1069 0.7304 0.0507
-5.750 -0.0491 0.01689 0.00861 -0.1058 0.7168 0.0520
-5.500 -0.0252 0.01654 0.00814 -0.1049 0.7048 0.0533
-5.250 -0.0022 0.01616 0.00773 -0.1039 0.6929 0.0548
-5.000 0.0219 0.01586 0.00736 -0.1030 0.6818 0.0568
-4.750 0.0462 0.01561 0.00700 -0.1022 0.6705 0.0595
-4.500 0.0701 0.01533 0.00668 -0.1013 0.6592 0.0628
-4.250 0.0947 0.01512 0.00637 -0.1005 0.6488 0.0672
-4.000 0.1190 0.01488 0.00611 -0.0996 0.6380 0.0729
-3.750 0.1436 0.01467 0.00586 -0.0988 0.6279 0.0809
-3.500 0.1680 0.01448 0.00562 -0.0980 0.6171 0.0924
-3.250 0.1925 0.01427 0.00540 -0.0972 0.6068 0.1070
-3.000 0.2167 0.01406 0.00518 -0.0964 0.5968 0.1257
-2.750 0.2405 0.01380 0.00509 -0.0956 0.5867 0.1633
-2.500 0.2651 0.01373 0.00502 -0.0948 0.5766 0.2010
-2.250 0.2899 0.01366 0.00497 -0.0940 0.5653 0.2246
-2.000 0.3144 0.01363 0.00493 -0.0932 0.5547 0.2459
-1.750 0.3388 0.01360 0.00490 -0.0924 0.5437 0.2683
-1.500 0.3632 0.01357 0.00489 -0.0916 0.5328 0.2905
-1.250 0.3871 0.01358 0.00487 -0.0906 0.5213 0.3096
-1.000 0.4112 0.01357 0.00485 -0.0898 0.5091 0.3259
-0.750 0.4350 0.01359 0.00484 -0.0888 0.4969 0.3419
-0.500 0.4584 0.01363 0.00484 -0.0878 0.4851 0.3594
-0.250 0.4818 0.01366 0.00486 -0.0868 0.4729 0.3781
0.000 0.5050 0.01370 0.00490 -0.0858 0.4608 0.4001
0.250 0.5273 0.01377 0.00495 -0.0846 0.4489 0.4264
0.500 0.5497 0.01384 0.00501 -0.0834 0.4368 0.4535
0.750 0.5720 0.01389 0.00507 -0.0823 0.4256 0.4797
1.250 0.6154 0.01400 0.00523 -0.0797 0.4059 0.5362
1.500 0.6357 0.01402 0.00534 -0.0782 0.3972 0.5780
1.750 0.6553 0.01391 0.00548 -0.0764 0.3885 0.6637
2.000 0.7536 0.01391 0.00592 -0.0909 0.3739 0.9990
2.250 0.7747 0.01417 0.00605 -0.0896 0.3669 1.0000
2.500 0.7954 0.01440 0.00619 -0.0882 0.3610 1.0000
2.750 0.8162 0.01463 0.00635 -0.0868 0.3551 1.0000
3.000 0.8361 0.01490 0.00652 -0.0853 0.3498 1.0000
3.250 0.8566 0.01516 0.00670 -0.0840 0.3452 1.0000
3.500 0.8777 0.01539 0.00689 -0.0827 0.3402 1.0000
3.750 0.8978 0.01566 0.00709 -0.0813 0.3353 1.0000
4.000 0.9171 0.01598 0.00730 -0.0797 0.3311 1.0000
4.250 0.9380 0.01623 0.00753 -0.0785 0.3270 1.0000
4.500 0.9585 0.01650 0.00777 -0.0772 0.3228 1.0000
4.750 0.9783 0.01679 0.00801 -0.0758 0.3190 1.0000
5.000 0.9968 0.01711 0.00828 -0.0741 0.3157 1.0000
5.250 1.0152 0.01745 0.00855 -0.0725 0.3127 1.0000
5.500 1.0351 0.01772 0.00884 -0.0712 0.3097 1.0000
5.750 1.0545 0.01802 0.00914 -0.0697 0.3066 1.0000
6.000 1.0734 0.01834 0.00945 -0.0683 0.3034 1.0000
6.250 1.0919 0.01869 0.00977 -0.0668 0.3005 1.0000
6.500 1.1101 0.01909 0.01011 -0.0653 0.2977 1.0000
6.750 1.1293 0.01947 0.01047 -0.0640 0.2950 1.0000
7.000 1.1484 0.01981 0.01085 -0.0627 0.2922 1.0000
7.250 1.1674 0.02018 0.01125 -0.0614 0.2895 1.0000
7.500 1.1861 0.02057 0.01166 -0.0602 0.2870 1.0000
7.750 1.2045 0.02100 0.01208 -0.0589 0.2845 1.0000
8.000 1.2228 0.02144 0.01251 -0.0576 0.2822 1.0000
8.250 1.2418 0.02193 0.01296 -0.0566 0.2802 1.0000
8.500 1.2609 0.02239 0.01345 -0.0555 0.2782 1.0000
8.750 1.2788 0.02285 0.01398 -0.0543 0.2761 1.0000
9.000 1.2965 0.02334 0.01453 -0.0531 0.2739 1.0000
9.250 1.3136 0.02385 0.01509 -0.0519 0.2717 1.0000
9.500 1.3303 0.02438 0.01566 -0.0506 0.2694 1.0000
9.750 1.3466 0.02493 0.01623 -0.0494 0.2672 1.0000
10.000 1.3640 0.02550 0.01681 -0.0484 0.2653 1.0000
10.250 1.3825 0.02609 0.01738 -0.0475 0.2636 1.0000
10.500 1.3996 0.02671 0.01806 -0.0465 0.2619 1.0000
10.750 1.4147 0.02738 0.01884 -0.0453 0.2602 1.0000
11.000 1.4296 0.02808 0.01963 -0.0441 0.2585 1.0000
11.250 1.4441 0.02881 0.02045 -0.0430 0.2566 1.0000
11.500 1.4583 0.02957 0.02128 -0.0418 0.2547 1.0000
11.750 1.4717 0.03035 0.02213 -0.0407 0.2527 1.0000
12.000 1.4856 0.03114 0.02297 -0.0396 0.2509 1.0000
12.250 1.5007 0.03191 0.02377 -0.0387 0.2493 1.0000
12.500 1.5177 0.03265 0.02452 -0.0380 0.2478 1.0000
12.750 1.5326 0.03350 0.02544 -0.0371 0.2463 1.0000
13.000 1.5404 0.03468 0.02676 -0.0358 0.2446 1.0000
13.250 1.5484 0.03589 0.02811 -0.0346 0.2427 1.0000
13.500 1.5569 0.03711 0.02946 -0.0335 0.2408 1.0000
13.750 1.5645 0.03839 0.03084 -0.0324 0.2388 1.0000
14.000 1.5726 0.03965 0.03219 -0.0315 0.2368 1.0000
14.250 1.5806 0.04087 0.03345 -0.0306 0.2342 1.0000
14.500 1.5942 0.04175 0.03429 -0.0299 0.2316 1.0000
14.750 1.5905 0.04399 0.03673 -0.0288 0.2290 1.0000
15.000 1.5865 0.04636 0.03927 -0.0280 0.2258 1.0000
15.250 1.5862 0.04853 0.04156 -0.0273 0.2227 1.0000
15.500 1.5881 0.05053 0.04362 -0.0269 0.2197 1.0000
15.750 1.5973 0.05187 0.04492 -0.0265 0.2168 1.0000
16.000 1.5907 0.05499 0.04824 -0.0263 0.2142 1.0000
16.250 1.5826 0.05841 0.05185 -0.0262 0.2113 1.0000
16.500 1.5765 0.06170 0.05528 -0.0264 0.2083 1.0000
16.750 1.5745 0.06456 0.05822 -0.0266 0.2052 1.0000
17.000 1.5808 0.06642 0.06007 -0.0266 0.2024 1.0000
17.250 1.5634 0.07141 0.06528 -0.0274 0.1995 1.0000
17.500 1.5412 0.07722 0.07129 -0.0286 0.1958 1.0000
17.750 1.5259 0.08224 0.07645 -0.0297 0.1926 1.0000
18.000 1.5281 0.08485 0.07906 -0.0302 0.1892 1.0000
18.250 1.4998 0.09194 0.08635 -0.0322 0.1860 1.0000
18.500 1.4214 0.10693 0.10165 -0.0372 0.1814 1.0000
18.750 1.4067 0.11245 0.10724 -0.0392 0.1773 1.0000
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