GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 500,000 Max Cl/Cd: 100.54 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe14k-il-500000.txt Download as CSV file: xf-goe14k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4705 0.14675 0.14437 -0.0457 0.9930 0.0235
-13.500 -0.4573 0.14483 0.14243 -0.0450 0.9917 0.0246
-12.250 -0.7681 0.04656 0.04349 -0.1010 0.9776 0.0159
-12.000 -0.7973 0.04088 0.03735 -0.0997 0.9751 0.0159
-11.750 -0.7757 0.04212 0.03876 -0.0981 0.9702 0.0166
-11.500 -0.7866 0.03917 0.03551 -0.0950 0.9662 0.0166
-11.250 -0.7831 0.03719 0.03331 -0.0931 0.9643 0.0172
-11.000 -0.7958 0.03586 0.03180 -0.0866 0.9568 0.0177
-10.750 -0.7982 0.03315 0.02873 -0.0829 0.9536 0.0178
-10.500 -0.7875 0.03079 0.02603 -0.0812 0.9520 0.0181
-10.250 -0.7923 0.02989 0.02493 -0.0752 0.9446 0.0185
-10.000 -0.7774 0.02854 0.02333 -0.0734 0.9423 0.0188
-9.750 -0.7678 0.02575 0.02025 -0.0712 0.9406 0.0198
-9.500 -0.7439 0.02498 0.01941 -0.0711 0.9396 0.0204
-9.250 -0.7426 0.02490 0.01929 -0.0659 0.9329 0.0209
-9.000 -0.7245 0.02386 0.01810 -0.0643 0.9306 0.0217
-8.750 -0.7016 0.02314 0.01723 -0.0638 0.9291 0.0226
-8.500 -0.6763 0.02246 0.01636 -0.0635 0.9280 0.0235
-8.250 -0.6540 0.02085 0.01462 -0.0630 0.9271 0.0248
-8.000 -0.6261 0.02044 0.01420 -0.0634 0.9264 0.0263
-7.750 -0.6286 0.02033 0.01402 -0.0571 0.9192 0.0269
-7.500 -0.6057 0.01981 0.01339 -0.0563 0.9174 0.0283
-7.250 -0.5817 0.01914 0.01263 -0.0558 0.9161 0.0302
-7.000 -0.5555 0.01871 0.01219 -0.0557 0.9150 0.0319
-6.750 -0.5273 0.01844 0.01188 -0.0560 0.9142 0.0343
-6.500 -0.4980 0.01816 0.01150 -0.0564 0.9136 0.0360
-6.250 -0.4708 0.01744 0.01079 -0.0567 0.9130 0.0391
-6.000 -0.4773 0.01766 0.01098 -0.0495 0.9053 0.0402
-5.750 -0.4529 0.01748 0.01075 -0.0489 0.9036 0.0429
-5.500 -0.4271 0.01712 0.01031 -0.0486 0.9024 0.0459
-5.250 -0.4010 0.01663 0.00985 -0.0485 0.9015 0.0495
-5.000 -0.3727 0.01637 0.00955 -0.0488 0.9007 0.0528
-4.750 -0.3429 0.01628 0.00940 -0.0494 0.9001 0.0554
-4.500 -0.3162 0.01545 0.00856 -0.0494 0.8995 0.0600
-4.250 -0.3258 0.01585 0.00893 -0.0415 0.8921 0.0615
-4.000 -0.3037 0.01570 0.00876 -0.0404 0.8900 0.0648
-3.750 -0.2783 0.01553 0.00854 -0.0401 0.8887 0.0675
-3.500 -0.2526 0.01517 0.00816 -0.0398 0.8876 0.0710
-3.250 -0.2250 0.01488 0.00788 -0.0399 0.8868 0.0757
-3.000 -0.1956 0.01464 0.00762 -0.0404 0.8861 0.0803
-2.750 -0.1649 0.01434 0.00733 -0.0411 0.8856 0.0872
-2.500 -0.1335 0.01398 0.00707 -0.0421 0.8852 0.1053
-2.250 -0.1248 0.01391 0.00732 -0.0384 0.8813 0.1797
-1.250 0.1668 0.01189 0.00811 -0.0807 0.8905 0.9143
-1.000 0.1940 0.01214 0.00833 -0.0804 0.8891 0.9341
-0.750 0.2298 0.01235 0.00850 -0.0819 0.8884 0.9483
-0.500 0.2822 0.01248 0.00860 -0.0872 0.8886 0.9555
0.000 0.3986 0.01238 0.00845 -0.1003 0.8894 0.9674
0.250 0.4485 0.01242 0.00849 -0.1051 0.8892 0.9741
0.500 0.5044 0.01223 0.00831 -0.1116 0.8894 0.9766
0.750 0.5595 0.01194 0.00803 -0.1177 0.8889 0.9796
1.000 0.6347 0.01112 0.00720 -0.1280 0.8866 0.9799
1.250 0.7013 0.01068 0.00675 -0.1367 0.8829 0.9811
1.500 0.7342 0.01046 0.00655 -0.1377 0.8738 0.9868
1.750 0.7827 0.01004 0.00612 -0.1422 0.8627 0.9902
2.000 0.8302 0.00973 0.00581 -0.1465 0.8502 0.9951
2.250 0.8869 0.00922 0.00530 -0.1531 0.8390 0.9998
2.500 0.8938 0.00921 0.00532 -0.1485 0.8285 1.0000
2.750 0.9082 0.00920 0.00532 -0.1456 0.8172 1.0000
3.000 0.9191 0.00918 0.00527 -0.1417 0.7983 1.0000
3.250 0.9250 0.00920 0.00526 -0.1368 0.7759 1.0000
3.500 0.9220 0.00930 0.00523 -0.1297 0.7305 1.0000
3.750 0.9023 0.00976 0.00528 -0.1189 0.6458 1.0000
4.000 0.8776 0.01057 0.00563 -0.1074 0.5611 1.0000
4.250 0.8534 0.01154 0.00612 -0.0963 0.4632 1.0000
4.500 0.8432 0.01237 0.00659 -0.0885 0.3933 1.0000
4.750 0.8419 0.01307 0.00699 -0.0827 0.3267 1.0000
5.000 0.8374 0.01401 0.00745 -0.0764 0.2324 1.0000
5.250 0.8411 0.01475 0.00789 -0.0718 0.1731 1.0000
5.500 0.8482 0.01541 0.00830 -0.0679 0.1253 1.0000
5.750 0.8587 0.01595 0.00867 -0.0647 0.0960 1.0000
6.000 0.8718 0.01639 0.00904 -0.0620 0.0842 1.0000
6.250 0.8862 0.01675 0.00941 -0.0595 0.0767 1.0000
6.500 0.8997 0.01718 0.00983 -0.0569 0.0697 1.0000
6.750 0.9147 0.01755 0.01020 -0.0546 0.0642 1.0000
7.000 0.9283 0.01803 0.01067 -0.0520 0.0576 1.0000
7.250 0.9438 0.01838 0.01105 -0.0499 0.0530 1.0000
7.500 0.9562 0.01896 0.01162 -0.0472 0.0470 1.0000
7.750 0.9722 0.01933 0.01202 -0.0451 0.0430 1.0000
8.000 0.9835 0.02002 0.01268 -0.0423 0.0383 1.0000
8.250 0.9995 0.02041 0.01312 -0.0402 0.0356 1.0000
8.500 1.0145 0.02086 0.01355 -0.0382 0.0327 1.0000
8.750 1.0255 0.02162 0.01435 -0.0354 0.0305 1.0000
9.000 1.0393 0.02220 0.01500 -0.0330 0.0292 1.0000
9.250 1.0534 0.02274 0.01558 -0.0309 0.0274 1.0000
9.500 1.0657 0.02345 0.01629 -0.0284 0.0257 1.0000
9.750 1.0749 0.02447 0.01737 -0.0256 0.0244 1.0000
10.000 1.0874 0.02526 0.01825 -0.0232 0.0238 1.0000
10.250 1.1013 0.02590 0.01896 -0.0211 0.0228 1.0000
10.500 1.1151 0.02649 0.01958 -0.0191 0.0214 1.0000
10.750 1.1267 0.02738 0.02051 -0.0168 0.0208 1.0000
11.000 1.1353 0.02881 0.02199 -0.0142 0.0196 1.0000
11.250 1.1481 0.02972 0.02302 -0.0121 0.0192 1.0000
11.500 1.1607 0.03074 0.02416 -0.0101 0.0188 1.0000
11.750 1.1727 0.03170 0.02522 -0.0080 0.0183 1.0000
12.000 1.1835 0.03269 0.02631 -0.0058 0.0176 1.0000
12.250 1.1932 0.03357 0.02726 -0.0036 0.0169 1.0000
12.500 1.2024 0.03460 0.02836 -0.0014 0.0165 1.0000
12.750 1.2101 0.03588 0.02969 0.0009 0.0160 1.0000
13.000 1.2181 0.03744 0.03138 0.0031 0.0158 1.0000
13.250 1.2204 0.04000 0.03417 0.0058 0.0152 1.0000
13.500 1.2245 0.04165 0.03596 0.0083 0.0151 1.0000
13.750 1.2260 0.04312 0.03762 0.0110 0.0148 1.0000
14.000 1.2251 0.04511 0.03980 0.0138 0.0144 1.0000
14.250 1.2203 0.04776 0.04268 0.0167 0.0144 1.0000
14.500 1.2175 0.04978 0.04485 0.0192 0.0141 1.0000
14.750 1.2108 0.05236 0.04762 0.0217 0.0138 1.0000
15.000 1.2008 0.05545 0.05091 0.0241 0.0137 1.0000
15.250 1.1899 0.05867 0.05432 0.0261 0.0136 1.0000
15.500 1.1732 0.06274 0.05861 0.0279 0.0135 1.0000
15.750 1.1606 0.06647 0.06251 0.0290 0.0135 1.0000
16.000 1.1549 0.06944 0.06556 0.0295 0.0130 1.0000
16.250 1.1515 0.07226 0.06845 0.0296 0.0129 1.0000
16.500 1.1120 0.08090 0.07743 0.0284 0.0131 1.0000
16.750 1.0892 0.08764 0.08436 0.0263 0.0130 1.0000
17.000 1.0130 0.10621 0.10343 0.0169 0.0138 1.0000
17.250 0.9622 0.12247 0.11994 0.0071 0.0142 1.0000
17.500 0.7688 0.11803 0.11557 0.0162 0.0154 1.0000
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