GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 8K AIRFOIL (goe08k-il) Reynolds number: 200,000 Max Cl/Cd: 43.5 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe08k-il-200000-n5.txt Download as CSV file: xf-goe08k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 8K 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0392 0.10531 0.10105 -0.1433 0.9017 0.0190
-10.750 -0.0381 0.10177 0.09752 -0.1443 0.8994 0.0186
-10.500 -0.0357 0.09782 0.09358 -0.1462 0.8977 0.0189
-10.250 -0.0322 0.09370 0.08946 -0.1486 0.8964 0.0186
-10.000 -0.0300 0.08907 0.08483 -0.1515 0.8953 0.0196
-9.750 -0.0479 0.08770 0.08351 -0.1472 0.8878 0.0193
-9.500 -0.0550 0.08378 0.07962 -0.1478 0.8843 0.0191
-9.250 -0.0599 0.07904 0.07489 -0.1503 0.8822 0.0199
-9.000 -0.0664 0.07370 0.06956 -0.1537 0.8804 0.0200
-8.750 -0.1025 0.07261 0.06856 -0.1472 0.8700 0.0201
-8.500 -0.1190 0.06824 0.06419 -0.1485 0.8668 0.0191
-8.250 -0.1568 0.06726 0.06324 -0.1410 0.8569 0.0196
-8.000 -0.1762 0.06180 0.05770 -0.1404 0.8526 0.0198
-7.750 -0.2061 0.05859 0.05441 -0.1346 0.8447 0.0199
-7.500 -0.2296 0.05318 0.04882 -0.1306 0.8389 0.0199
-7.250 -0.2657 0.04200 0.03694 -0.1251 0.8360 0.0205
-7.000 -0.3214 0.03623 0.03045 -0.1113 0.8248 0.0210
-6.750 -0.3122 0.03381 0.02766 -0.1087 0.8232 0.0216
-6.500 -0.2778 0.03544 0.02950 -0.1103 0.8223 0.0226
-6.250 -0.2953 0.03362 0.02730 -0.1022 0.8151 0.0227
-6.000 -0.2824 0.03329 0.02684 -0.0999 0.8119 0.0239
-5.750 -0.2724 0.03066 0.02363 -0.0965 0.8100 0.0261
-5.500 -0.2521 0.02960 0.02233 -0.0953 0.8087 0.0277
-5.250 -0.2262 0.02955 0.02224 -0.0952 0.8077 0.0291
-4.750 -0.2160 0.02931 0.02164 -0.0869 0.7980 0.0327
-4.500 -0.1968 0.02854 0.02061 -0.0854 0.7962 0.0355
-4.250 -0.1737 0.02859 0.02065 -0.0848 0.7948 0.0376
-4.000 -0.1497 0.02810 0.01996 -0.0841 0.7938 0.0407
-3.750 -0.1246 0.02761 0.01914 -0.0835 0.7930 0.0444
-3.500 -0.1294 0.02796 0.01939 -0.0776 0.7859 0.0454
-3.250 -0.1130 0.02785 0.01929 -0.0759 0.7831 0.0476
-3.000 -0.0910 0.02761 0.01896 -0.0750 0.7815 0.0507
-2.750 -0.0670 0.02727 0.01847 -0.0744 0.7803 0.0534
-2.500 -0.0416 0.02712 0.01813 -0.0739 0.7793 0.0560
-2.250 -0.0151 0.02630 0.01729 -0.0740 0.7786 0.0587
-1.750 -0.0018 0.02702 0.01798 -0.0668 0.7690 0.0623
-1.500 0.0205 0.02685 0.01774 -0.0660 0.7673 0.0639
-1.250 0.0449 0.02661 0.01744 -0.0656 0.7660 0.0654
-1.000 0.0705 0.02641 0.01718 -0.0653 0.7650 0.0675
-0.750 0.0971 0.02623 0.01694 -0.0653 0.7641 0.0688
-0.500 0.1242 0.02578 0.01649 -0.0653 0.7634 0.0706
-0.250 0.1454 0.02568 0.01640 -0.0643 0.7616 0.0719
1.250 0.2357 0.02753 0.01813 -0.0526 0.7392 0.0818
1.500 0.2635 0.02736 0.01791 -0.0528 0.7372 0.0833
1.750 0.2935 0.02711 0.01766 -0.0533 0.7358 0.0870
2.000 0.3237 0.02689 0.01747 -0.0540 0.7347 0.0953
2.500 0.6402 0.02520 0.01837 -0.1133 0.7489 1.0000
2.750 0.6705 0.02493 0.01806 -0.1139 0.7482 1.0000
3.000 0.7010 0.02471 0.01782 -0.1146 0.7476 1.0000
3.500 0.7125 0.02655 0.01967 -0.1076 0.7347 1.0000
3.750 0.7139 0.02780 0.02092 -0.1036 0.7270 1.0000
4.000 0.7335 0.02805 0.02118 -0.1024 0.7231 1.0000
4.250 0.7608 0.02789 0.02102 -0.1025 0.7214 1.0000
4.500 0.7893 0.02769 0.02084 -0.1028 0.7201 1.0000
4.750 0.8198 0.02735 0.02051 -0.1034 0.7191 1.0000
5.000 0.8522 0.02691 0.02010 -0.1042 0.7182 1.0000
5.250 0.8842 0.02655 0.01978 -0.1051 0.7175 1.0000
5.750 0.9017 0.02808 0.02141 -0.0994 0.7039 1.0000
6.000 0.9238 0.02817 0.02155 -0.0987 0.7004 1.0000
7.000 0.9927 0.02906 0.02269 -0.0923 0.6749 1.0000
7.250 1.0227 0.02842 0.02211 -0.0925 0.6698 1.0000
8.250 1.0679 0.03059 0.02454 -0.0827 0.6186 1.0000
8.500 1.0889 0.03056 0.02456 -0.0817 0.6037 1.0000
8.750 1.1294 0.02909 0.02308 -0.0831 0.5806 1.0000
9.000 1.1767 0.02705 0.02060 -0.0851 0.5206 1.0000
9.250 1.1853 0.02774 0.02105 -0.0822 0.4798 1.0000
9.500 1.1844 0.02906 0.02214 -0.0780 0.4378 1.0000
9.750 1.1754 0.03094 0.02376 -0.0728 0.3861 1.0000
10.000 1.1616 0.03326 0.02572 -0.0673 0.3284 1.0000
10.250 1.1517 0.03548 0.02768 -0.0627 0.2775 1.0000
10.500 1.1443 0.03767 0.02961 -0.0587 0.2325 1.0000
10.750 1.1402 0.03973 0.03144 -0.0552 0.1925 1.0000
11.000 1.1385 0.04167 0.03318 -0.0521 0.1509 1.0000
11.250 1.1327 0.04399 0.03516 -0.0488 0.0981 1.0000
11.500 1.1329 0.04592 0.03694 -0.0462 0.0728 1.0000
11.750 1.1369 0.04761 0.03857 -0.0440 0.0543 1.0000
12.000 1.1409 0.04931 0.04022 -0.0419 0.0393 1.0000
12.250 1.1462 0.05096 0.04187 -0.0400 0.0323 1.0000
12.500 1.1529 0.05252 0.04349 -0.0383 0.0285 1.0000
12.750 1.1569 0.05436 0.04539 -0.0364 0.0260 1.0000
13.000 1.1599 0.05633 0.04745 -0.0345 0.0239 1.0000
13.250 1.1663 0.05799 0.04923 -0.0330 0.0226 1.0000
13.500 1.1707 0.05986 0.05120 -0.0314 0.0214 1.0000
13.750 1.1745 0.06181 0.05326 -0.0299 0.0201 1.0000
14.000 1.1755 0.06406 0.05558 -0.0282 0.0190 1.0000
14.250 1.1781 0.06620 0.05782 -0.0267 0.0181 1.0000
14.500 1.1833 0.06811 0.05983 -0.0255 0.0168 1.0000
14.750 1.1864 0.07025 0.06206 -0.0242 0.0159 1.0000
15.000 1.1892 0.07243 0.06433 -0.0230 0.0156 1.0000
15.250 1.1908 0.07474 0.06669 -0.0218 0.0151 1.0000
15.500 1.1923 0.07709 0.06912 -0.0206 0.0146 1.0000
15.750 1.1962 0.07920 0.07138 -0.0195 0.0142 1.0000
16.000 1.2005 0.08130 0.07361 -0.0185 0.0136 1.0000
16.250 1.2039 0.08351 0.07593 -0.0175 0.0129 1.0000
16.500 1.2088 0.08553 0.07806 -0.0167 0.0129 1.0000
16.750 1.2119 0.08782 0.08044 -0.0161 0.0124 1.0000
17.000 1.2143 0.09019 0.08286 -0.0154 0.0119 1.0000
17.250 1.2169 0.09248 0.08520 -0.0148 0.0115 1.0000
17.500 1.2197 0.09493 0.08785 -0.0142 0.0111 1.0000
17.750 1.2220 0.09740 0.09049 -0.0137 0.0109 1.0000
18.000 1.2244 0.09987 0.09313 -0.0131 0.0107 1.0000
18.250 1.2236 0.10284 0.09627 -0.0129 0.0103 1.0000
18.500 1.2234 0.10573 0.09936 -0.0127 0.0102 1.0000
18.750 1.2207 0.10904 0.10283 -0.0128 0.0099 1.0000
19.000 1.2178 0.11243 0.10638 -0.0130 0.0098 1.0000
19.250 1.2139 0.11606 0.11020 -0.0135 0.0097 1.0000
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