GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 200,000 Max Cl/Cd: 49.96 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe559-il-200000-n5.txt Download as CSV file: xf-goe559-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 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 -0.3226 0.09162 0.08854 -0.0395 1.0000 0.0058
-8.000 -0.3229 0.08860 0.08558 -0.0405 1.0000 0.0060
-7.750 -0.3245 0.08578 0.08282 -0.0408 1.0000 0.0059
-7.500 -0.3175 0.08185 0.07894 -0.0457 0.9879 0.0062
-7.250 -0.3025 0.07670 0.07379 -0.0536 0.9639 0.0062
-7.000 -0.2818 0.07104 0.06806 -0.0622 0.9384 0.0062
-6.750 -0.2499 0.06591 0.06268 -0.0721 0.9105 0.0065
-6.500 -0.2299 0.06127 0.05786 -0.0765 0.8817 0.0065
-5.750 -0.1975 0.04872 0.04459 -0.0803 0.7737 0.0076
-5.500 -0.1876 0.04547 0.04105 -0.0799 0.7485 0.0086
-5.250 -0.1734 0.04267 0.03794 -0.0792 0.7286 0.0091
-5.000 -0.1575 0.03999 0.03491 -0.0783 0.7119 0.0097
-4.750 -0.1396 0.03751 0.03209 -0.0773 0.6969 0.0104
-4.500 -0.1191 0.03542 0.02965 -0.0759 0.6828 0.0114
-4.250 -0.0927 0.03514 0.02887 -0.0740 0.6687 0.0126
-4.000 -0.0715 0.03380 0.02711 -0.0725 0.6554 0.0128
-3.750 -0.0557 0.02940 0.02244 -0.0715 0.6438 0.0136
-3.500 -0.0372 0.02640 0.01921 -0.0708 0.6315 0.0151
-3.250 -0.0150 0.02455 0.01700 -0.0697 0.6191 0.0171
-3.000 0.0100 0.02342 0.01547 -0.0684 0.6071 0.0202
-2.750 0.0330 0.02152 0.01321 -0.0674 0.5961 0.0246
-2.500 0.0566 0.02006 0.01144 -0.0667 0.5855 0.0353
-2.250 0.0815 0.01866 0.00979 -0.0660 0.5758 0.0449
-2.000 0.1097 0.01781 0.00869 -0.0651 0.5675 0.0376
-1.750 0.1388 0.01691 0.00763 -0.0641 0.5596 0.0183
-1.500 0.1657 0.01610 0.00667 -0.0632 0.5528 0.0104
-1.250 0.1902 0.01524 0.00571 -0.0623 0.5461 0.0085
-1.000 0.2146 0.01472 0.00503 -0.0614 0.5401 0.0073
-0.750 0.2394 0.01434 0.00443 -0.0608 0.5337 0.0066
-0.500 0.2611 0.01358 0.00353 -0.0598 0.5283 0.0093
-0.250 0.2863 0.01331 0.00305 -0.0594 0.5230 0.0110
0.000 0.3120 0.01317 0.00268 -0.0590 0.5178 0.0124
0.250 0.3294 0.01191 0.00239 -0.0576 0.5139 0.4208
0.500 0.4445 0.01065 0.00256 -0.0760 0.5067 1.0000
0.750 0.4677 0.01075 0.00257 -0.0755 0.5026 1.0000
1.000 0.4906 0.01087 0.00262 -0.0748 0.4989 1.0000
1.250 0.5143 0.01097 0.00274 -0.0744 0.4949 1.0000
1.500 0.5378 0.01107 0.00287 -0.0739 0.4908 1.0000
1.750 0.5556 0.01112 0.00279 -0.0721 0.4492 1.0000
2.000 0.5476 0.01366 0.00349 -0.0665 0.0220 1.0000
2.250 0.5691 0.01397 0.00399 -0.0653 0.0110 1.0000
2.500 0.5903 0.01430 0.00448 -0.0641 0.0103 1.0000
2.750 0.6108 0.01469 0.00503 -0.0628 0.0074 1.0000
3.000 0.6299 0.01522 0.00591 -0.0611 0.0074 1.0000
3.250 0.6473 0.01585 0.00676 -0.0592 0.0080 1.0000
3.500 0.6605 0.01674 0.00785 -0.0566 0.0087 1.0000
3.750 0.6688 0.01786 0.00909 -0.0532 0.0096 1.0000
4.000 0.6711 0.01940 0.01063 -0.0490 0.0112 1.0000
4.250 0.6967 0.01943 0.01085 -0.0479 0.0165 1.0000
4.500 0.7087 0.02050 0.01190 -0.0448 0.0264 1.0000
5.500 0.8147 0.02949 0.02053 -0.0430 0.0192 1.0000
5.750 0.8197 0.02822 0.01977 -0.0381 0.0158 1.0000
6.000 0.8509 0.03109 0.02265 -0.0387 0.0123 1.0000
6.250 0.8445 0.02135 0.01341 -0.0352 0.0106 1.0000
6.500 0.8574 0.02055 0.01298 -0.0315 0.0087 1.0000
6.750 0.8782 0.02272 0.01535 -0.0301 0.0074 1.0000
7.000 0.8957 0.02573 0.01856 -0.0288 0.0068 1.0000
7.250 0.9112 0.03033 0.02331 -0.0281 0.0063 1.0000
7.500 0.9242 0.03618 0.02927 -0.0273 0.0060 1.0000
7.750 0.9327 0.03895 0.03232 -0.0246 0.0059 1.0000
8.000 0.9386 0.04140 0.03508 -0.0215 0.0058 1.0000
8.250 0.9436 0.04345 0.03740 -0.0183 0.0057 1.0000
8.500 0.9490 0.04481 0.03906 -0.0147 0.0055 1.0000
8.750 0.9514 0.04720 0.04169 -0.0116 0.0052 1.0000
9.000 0.9496 0.05005 0.04475 -0.0085 0.0050 1.0000
9.250 0.9422 0.05288 0.04776 -0.0051 0.0049 1.0000
9.500 0.9297 0.05559 0.05063 -0.0015 0.0048 1.0000
9.750 0.9151 0.05846 0.05366 0.0015 0.0048 1.0000
10.000 0.8982 0.06156 0.05692 0.0038 0.0048 1.0000
10.250 0.8798 0.06501 0.06052 0.0054 0.0048 1.0000
10.500 0.8605 0.06877 0.06443 0.0063 0.0048 1.0000
10.750 0.8397 0.07288 0.06868 0.0066 0.0048 1.0000
11.000 0.8180 0.07740 0.07334 0.0063 0.0049 1.0000
11.250 0.7959 0.08208 0.07815 0.0054 0.0050 1.0000
11.500 0.7738 0.08699 0.08317 0.0040 0.0051 1.0000
11.750 0.7501 0.09188 0.08819 0.0023 0.0052 1.0000
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Polar data table (+)
Polar graphs
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