GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 200,000 Max Cl/Cd: 75.29 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe550-il-200000-n5.txt Download as CSV file: xf-goe550-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6474 0.07927 0.07499 -0.0651 1.0000 0.0414
-13.250 -0.7026 0.06806 0.06364 -0.0717 1.0000 0.0413
-13.000 -0.7391 0.06050 0.05597 -0.0759 1.0000 0.0413
-12.750 -0.7700 0.05426 0.04965 -0.0789 1.0000 0.0414
-12.500 -0.8010 0.04863 0.04395 -0.0811 1.0000 0.0415
-12.250 -0.8370 0.04361 0.03891 -0.0820 1.0000 0.0413
-12.000 -0.8598 0.03806 0.03315 -0.0858 1.0000 0.0415
-11.750 -0.8672 0.03528 0.03014 -0.0855 1.0000 0.0422
-11.500 -0.8555 0.03323 0.02800 -0.0866 0.9981 0.0432
-11.250 -0.8269 0.03146 0.02613 -0.0900 0.9939 0.0447
-11.000 -0.7997 0.02987 0.02438 -0.0926 0.9892 0.0465
-10.750 -0.7703 0.02832 0.02260 -0.0953 0.9848 0.0484
-10.500 -0.7427 0.02690 0.02092 -0.0972 0.9799 0.0500
-10.250 -0.7149 0.02562 0.01962 -0.0988 0.9749 0.0518
-10.000 -0.6833 0.02459 0.01849 -0.1009 0.9712 0.0538
-9.750 -0.6574 0.02361 0.01737 -0.1016 0.9644 0.0557
-9.500 -0.6257 0.02263 0.01619 -0.1032 0.9604 0.0578
-9.250 -0.5989 0.02168 0.01517 -0.1039 0.9541 0.0599
-9.000 -0.5690 0.02087 0.01430 -0.1050 0.9487 0.0622
-8.750 -0.5355 0.02008 0.01341 -0.1067 0.9453 0.0648
-8.500 -0.5093 0.01941 0.01260 -0.1068 0.9374 0.0673
-8.250 -0.4771 0.01868 0.01183 -0.1081 0.9326 0.0706
-8.000 -0.4436 0.01808 0.01116 -0.1096 0.9279 0.0746
-7.750 -0.4144 0.01755 0.01049 -0.1100 0.9199 0.0785
-7.500 -0.3794 0.01694 0.00987 -0.1117 0.9151 0.0833
-7.250 -0.3496 0.01650 0.00932 -0.1122 0.9071 0.0889
-7.000 -0.3162 0.01599 0.00878 -0.1135 0.9009 0.0951
-6.750 -0.2833 0.01559 0.00825 -0.1145 0.8944 0.1021
-6.500 -0.2520 0.01515 0.00779 -0.1153 0.8867 0.1085
-6.250 -0.2176 0.01478 0.00731 -0.1167 0.8805 0.1161
-6.000 -0.1882 0.01443 0.00695 -0.1170 0.8717 0.1231
-5.750 -0.1544 0.01412 0.00654 -0.1182 0.8651 0.1310
-5.500 -0.1260 0.01387 0.00629 -0.1183 0.8557 0.1384
-5.250 -0.0937 0.01364 0.00598 -0.1190 0.8486 0.1469
-5.000 -0.0658 0.01349 0.00581 -0.1190 0.8392 0.1553
-4.750 -0.0349 0.01335 0.00560 -0.1194 0.8317 0.1642
-4.500 -0.0072 0.01326 0.00543 -0.1192 0.8226 0.1737
-4.250 0.0228 0.01320 0.00535 -0.1195 0.8149 0.1832
-4.000 0.0499 0.01316 0.00525 -0.1192 0.8058 0.1924
-3.750 0.0793 0.01313 0.00513 -0.1193 0.7984 0.2005
-3.500 0.1061 0.01306 0.00499 -0.1189 0.7895 0.2068
-3.000 0.1615 0.01299 0.00479 -0.1184 0.7729 0.2198
-2.750 0.1897 0.01293 0.00468 -0.1183 0.7654 0.2248
-2.500 0.2162 0.01289 0.00462 -0.1178 0.7564 0.2298
-2.250 0.2442 0.01286 0.00448 -0.1176 0.7485 0.2352
-2.000 0.2706 0.01280 0.00440 -0.1172 0.7391 0.2396
-1.750 0.2975 0.01276 0.00432 -0.1168 0.7288 0.2443
-1.500 0.3239 0.01273 0.00423 -0.1162 0.7169 0.2497
-1.250 0.3502 0.01272 0.00414 -0.1157 0.7050 0.2546
-1.000 0.3767 0.01266 0.00407 -0.1152 0.6951 0.2588
-0.750 0.4031 0.01264 0.00404 -0.1147 0.6852 0.2642
-0.500 0.4298 0.01266 0.00400 -0.1143 0.6757 0.2706
-0.250 0.4562 0.01262 0.00397 -0.1138 0.6663 0.2765
0.000 0.4824 0.01262 0.00396 -0.1133 0.6565 0.2824
0.250 0.5089 0.01263 0.00391 -0.1129 0.6471 0.2872
0.500 0.5347 0.01259 0.00391 -0.1123 0.6367 0.2913
0.750 0.5607 0.01258 0.00390 -0.1118 0.6271 0.2961
1.000 0.5868 0.01260 0.00390 -0.1113 0.6174 0.3019
1.250 0.6125 0.01260 0.00393 -0.1107 0.6072 0.3078
1.500 0.6381 0.01263 0.00395 -0.1101 0.5973 0.3146
1.750 0.6637 0.01266 0.00400 -0.1095 0.5869 0.3216
2.000 0.6892 0.01269 0.00406 -0.1089 0.5773 0.3297
2.250 0.7145 0.01274 0.00413 -0.1083 0.5677 0.3395
2.500 0.7396 0.01278 0.00423 -0.1076 0.5574 0.3527
2.750 0.7643 0.01282 0.00434 -0.1069 0.5474 0.3728
3.000 0.7887 0.01283 0.00450 -0.1062 0.5370 0.4109
3.250 0.8129 0.01283 0.00466 -0.1054 0.5273 0.4714
3.500 0.8365 0.01280 0.00481 -0.1045 0.5178 0.5382
4.000 0.8977 0.01233 0.00520 -0.1052 0.4934 1.0000
4.250 0.9211 0.01256 0.00535 -0.1042 0.4815 1.0000
4.500 0.9443 0.01278 0.00553 -0.1032 0.4693 1.0000
4.750 0.9678 0.01301 0.00573 -0.1023 0.4577 1.0000
5.000 0.9907 0.01325 0.00594 -0.1012 0.4463 1.0000
5.250 1.0131 0.01352 0.00616 -0.1001 0.4351 1.0000
5.500 1.0357 0.01377 0.00640 -0.0991 0.4231 1.0000
5.750 1.0578 0.01405 0.00665 -0.0979 0.4115 1.0000
6.000 1.0794 0.01435 0.00693 -0.0967 0.4010 1.0000
6.250 1.1010 0.01465 0.00721 -0.0955 0.3903 1.0000
6.500 1.1224 0.01496 0.00752 -0.0943 0.3804 1.0000
6.750 1.1430 0.01531 0.00784 -0.0930 0.3715 1.0000
7.000 1.1646 0.01562 0.00819 -0.0918 0.3628 1.0000
7.250 1.1843 0.01600 0.00854 -0.0903 0.3543 1.0000
7.500 1.2035 0.01636 0.00891 -0.0888 0.3427 1.0000
7.750 1.2209 0.01677 0.00930 -0.0869 0.3296 1.0000
8.000 1.2365 0.01719 0.00971 -0.0848 0.3163 1.0000
8.250 1.2510 0.01764 0.01014 -0.0825 0.3037 1.0000
8.500 1.2655 0.01810 0.01059 -0.0802 0.2916 1.0000
8.750 1.2810 0.01855 0.01107 -0.0781 0.2791 1.0000
9.000 1.2951 0.01905 0.01160 -0.0759 0.2654 1.0000
9.250 1.3075 0.01963 0.01217 -0.0735 0.2491 1.0000
9.500 1.3171 0.02035 0.01283 -0.0708 0.2285 1.0000
9.750 1.3228 0.02129 0.01365 -0.0678 0.1993 1.0000
10.000 1.3238 0.02257 0.01474 -0.0643 0.1669 1.0000
10.750 1.3313 0.02676 0.01870 -0.0560 0.1178 1.0000
11.000 1.3366 0.02813 0.02008 -0.0539 0.1095 1.0000
11.250 1.3416 0.02958 0.02155 -0.0519 0.1012 1.0000
11.500 1.3483 0.03098 0.02301 -0.0502 0.0934 1.0000
11.750 1.3527 0.03260 0.02465 -0.0485 0.0847 1.0000
12.000 1.3576 0.03426 0.02635 -0.0471 0.0760 1.0000
12.250 1.3607 0.03612 0.02822 -0.0456 0.0679 1.0000
12.500 1.3625 0.03818 0.03029 -0.0443 0.0619 1.0000
12.750 1.3636 0.04039 0.03253 -0.0431 0.0567 1.0000
13.000 1.3642 0.04271 0.03490 -0.0421 0.0527 1.0000
13.250 1.3647 0.04515 0.03740 -0.0413 0.0488 1.0000
13.500 1.3626 0.04795 0.04024 -0.0406 0.0458 1.0000
13.750 1.3639 0.05048 0.04288 -0.0400 0.0429 1.0000
14.000 1.3625 0.05339 0.04587 -0.0397 0.0403 1.0000
14.250 1.3594 0.05662 0.04916 -0.0395 0.0384 1.0000
14.500 1.3593 0.05960 0.05226 -0.0394 0.0364 1.0000
14.750 1.3575 0.06287 0.05562 -0.0396 0.0345 1.0000
15.000 1.3537 0.06650 0.05932 -0.0399 0.0331 1.0000
15.250 1.3503 0.07018 0.06309 -0.0404 0.0317 1.0000
15.500 1.3487 0.07370 0.06673 -0.0409 0.0302 1.0000
15.750 1.3459 0.07746 0.07059 -0.0416 0.0289 1.0000
16.000 1.3415 0.08153 0.07474 -0.0425 0.0280 1.0000
16.250 1.3351 0.08600 0.07928 -0.0437 0.0271 1.0000
16.500 1.3332 0.08984 0.08326 -0.0446 0.0262 1.0000
16.750 1.3303 0.09389 0.08743 -0.0458 0.0253 1.0000
17.000 1.3270 0.09807 0.09171 -0.0471 0.0245 1.0000
17.250 1.3235 0.10235 0.09609 -0.0485 0.0238 1.0000
17.500 1.3195 0.10676 0.10057 -0.0501 0.0232 1.0000
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