GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 500,000 Max Cl/Cd: 90.42 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe585-il-500000.txt Download as CSV file: xf-goe585-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4091 0.08559 0.08331 -0.0273 1.0000 0.0263
-8.250 -0.4095 0.08311 0.08085 -0.0273 1.0000 0.0269
-8.000 -0.4143 0.08059 0.07837 -0.0269 1.0000 0.0276
-7.750 -0.4261 0.07832 0.07616 -0.0257 1.0000 0.0282
-7.500 -0.4358 0.07505 0.07294 -0.0263 1.0000 0.0291
-7.000 -0.3867 0.04448 0.04243 -0.0449 0.9942 0.0318
-6.750 -0.3665 0.04193 0.03985 -0.0468 0.9910 0.0326
-6.500 -0.3436 0.03834 0.03620 -0.0506 0.9876 0.0336
-6.250 -0.3184 0.03305 0.03079 -0.0565 0.9848 0.0358
-6.000 -0.3550 0.02509 0.02094 -0.0634 0.9822 0.0317
-5.750 -0.3305 0.02162 0.01702 -0.0639 0.9775 0.0318
-5.500 -0.3000 0.01954 0.01472 -0.0653 0.9746 0.0329
-5.250 -0.2655 0.01884 0.01400 -0.0670 0.9727 0.0345
-5.000 -0.2311 0.01717 0.01204 -0.0686 0.9711 0.0353
-4.750 -0.2044 0.01586 0.01050 -0.0684 0.9656 0.0359
-4.500 -0.1711 0.01488 0.00936 -0.0695 0.9625 0.0371
-4.250 -0.1356 0.01401 0.00834 -0.0709 0.9603 0.0380
-4.000 -0.0975 0.01312 0.00732 -0.0729 0.9586 0.0386
-3.750 -0.0630 0.01241 0.00652 -0.0740 0.9532 0.0390
-3.500 -0.0292 0.01121 0.00522 -0.0751 0.9471 0.0403
-3.250 0.0063 0.01041 0.00437 -0.0765 0.9422 0.0417
-3.000 0.0352 0.00994 0.00388 -0.0764 0.9329 0.0429
-2.750 0.0668 0.00952 0.00343 -0.0769 0.9243 0.0442
-2.500 0.0977 0.00917 0.00303 -0.0772 0.9144 0.0456
-2.250 0.1251 0.00891 0.00273 -0.0768 0.9027 0.0472
-2.000 0.1529 0.00869 0.00247 -0.0765 0.8912 0.0494
-1.750 0.1803 0.00842 0.00219 -0.0761 0.8793 0.0547
-1.500 0.2072 0.00822 0.00199 -0.0756 0.8664 0.0662
-1.250 0.2331 0.00795 0.00186 -0.0750 0.8520 0.1151
-1.000 0.2590 0.00779 0.00177 -0.0743 0.8367 0.1481
-0.750 0.2845 0.00762 0.00167 -0.0737 0.8198 0.1859
-0.500 0.3090 0.00734 0.00164 -0.0729 0.8013 0.2805
-0.250 0.3333 0.00708 0.00161 -0.0721 0.7827 0.3788
0.000 0.3494 0.00619 0.00160 -0.0697 0.7644 0.6837
0.250 0.4203 0.00571 0.00170 -0.0783 0.7437 0.9843
0.500 0.4710 0.00582 0.00166 -0.0832 0.7226 1.0000
0.750 0.4940 0.00595 0.00165 -0.0819 0.7027 1.0000
1.000 0.5171 0.00606 0.00166 -0.0808 0.6813 1.0000
1.250 0.5401 0.00619 0.00167 -0.0795 0.6593 1.0000
1.500 0.5630 0.00632 0.00170 -0.0783 0.6348 1.0000
1.750 0.5853 0.00649 0.00173 -0.0770 0.6048 1.0000
2.000 0.6067 0.00671 0.00178 -0.0755 0.5656 1.0000
2.250 0.6269 0.00702 0.00185 -0.0738 0.5133 1.0000
2.500 0.6468 0.00741 0.00197 -0.0721 0.4626 1.0000
2.750 0.6681 0.00774 0.00212 -0.0707 0.4258 1.0000
3.000 0.6903 0.00804 0.00227 -0.0695 0.3989 1.0000
3.250 0.7131 0.00830 0.00243 -0.0684 0.3770 1.0000
3.500 0.7360 0.00856 0.00259 -0.0674 0.3584 1.0000
3.750 0.7592 0.00881 0.00275 -0.0664 0.3414 1.0000
4.000 0.7826 0.00904 0.00292 -0.0654 0.3265 1.0000
4.250 0.8063 0.00927 0.00311 -0.0645 0.3131 1.0000
4.500 0.8301 0.00949 0.00329 -0.0637 0.3007 1.0000
4.750 0.8539 0.00972 0.00348 -0.0628 0.2874 1.0000
5.000 0.8776 0.00996 0.00368 -0.0620 0.2740 1.0000
5.250 0.9014 0.01020 0.00388 -0.0611 0.2622 1.0000
5.500 0.9249 0.01046 0.00410 -0.0603 0.2511 1.0000
5.750 0.9488 0.01069 0.00431 -0.0595 0.2406 1.0000
6.000 0.9729 0.01092 0.00456 -0.0587 0.2318 1.0000
6.250 0.9962 0.01121 0.00481 -0.0579 0.2224 1.0000
6.500 1.0201 0.01144 0.00503 -0.0571 0.2113 1.0000
6.750 1.0440 0.01168 0.00528 -0.0564 0.2007 1.0000
7.000 1.0674 0.01196 0.00555 -0.0556 0.1897 1.0000
7.250 1.0905 0.01226 0.00583 -0.0547 0.1785 1.0000
7.500 1.1134 0.01258 0.00612 -0.0539 0.1666 1.0000
7.750 1.1362 0.01292 0.00644 -0.0530 0.1524 1.0000
8.000 1.1584 0.01330 0.00679 -0.0521 0.1329 1.0000
8.250 1.1781 0.01393 0.00725 -0.0508 0.1030 1.0000
8.500 1.1955 0.01477 0.00790 -0.0493 0.0756 1.0000
8.750 1.2139 0.01550 0.00856 -0.0478 0.0589 1.0000
9.000 1.2306 0.01639 0.00936 -0.0461 0.0426 1.0000
9.250 1.2476 0.01722 0.01014 -0.0444 0.0310 1.0000
9.500 1.2639 0.01808 0.01101 -0.0426 0.0260 1.0000
9.750 1.2813 0.01878 0.01177 -0.0410 0.0234 1.0000
10.000 1.2933 0.01987 0.01290 -0.0386 0.0210 1.0000
10.250 1.3096 0.02055 0.01369 -0.0368 0.0201 1.0000
10.500 1.3240 0.02130 0.01451 -0.0348 0.0188 1.0000
10.750 1.3345 0.02213 0.01540 -0.0322 0.0177 1.0000
11.000 1.3392 0.02325 0.01659 -0.0287 0.0170 1.0000
11.250 1.3365 0.02484 0.01829 -0.0245 0.0163 1.0000
11.500 1.3451 0.02580 0.01935 -0.0221 0.0160 1.0000
11.750 1.3518 0.02691 0.02057 -0.0196 0.0155 1.0000
12.000 1.3557 0.02827 0.02205 -0.0170 0.0152 1.0000
12.250 1.3600 0.02966 0.02355 -0.0147 0.0147 1.0000
12.500 1.3620 0.03131 0.02530 -0.0125 0.0143 1.0000
12.750 1.3644 0.03302 0.02710 -0.0107 0.0140 1.0000
13.000 1.3645 0.03504 0.02922 -0.0090 0.0137 1.0000
13.250 1.3637 0.03727 0.03153 -0.0077 0.0133 1.0000
13.500 1.3600 0.03996 0.03432 -0.0066 0.0131 1.0000
13.750 1.3533 0.04316 0.03763 -0.0058 0.0128 1.0000
14.000 1.3439 0.04690 0.04151 -0.0052 0.0125 1.0000
14.250 1.3433 0.04976 0.04451 -0.0054 0.0123 1.0000
14.500 1.3402 0.05307 0.04797 -0.0057 0.0122 1.0000
14.750 1.3359 0.05667 0.05171 -0.0063 0.0121 1.0000
15.000 1.3305 0.06058 0.05578 -0.0072 0.0120 1.0000
15.250 1.3239 0.06483 0.06018 -0.0085 0.0118 1.0000
15.500 1.3169 0.06937 0.06486 -0.0102 0.0117 1.0000
15.750 1.3085 0.07429 0.06992 -0.0121 0.0116 1.0000
16.000 1.3000 0.07941 0.07518 -0.0144 0.0115 1.0000
16.250 1.2898 0.08499 0.08091 -0.0169 0.0115 1.0000
16.500 1.2791 0.09086 0.08694 -0.0198 0.0114 1.0000
16.750 1.2670 0.09712 0.09334 -0.0230 0.0114 1.0000
17.000 1.2559 0.10342 0.09978 -0.0264 0.0113 1.0000
17.250 1.2415 0.11049 0.10701 -0.0302 0.0113 1.0000
17.500 1.2279 0.11762 0.11428 -0.0343 0.0112 1.0000
17.750 1.2119 0.12545 0.12226 -0.0388 0.0113 1.0000
18.000 1.1961 0.13356 0.13053 -0.0437 0.0113 1.0000
18.250 1.1782 0.14238 0.13950 -0.0490 0.0114 1.0000
18.500 1.1583 0.15211 0.14939 -0.0551 0.0115 1.0000
18.750 1.1342 0.16348 0.16091 -0.0622 0.0116 1.0000
19.000 1.1021 0.17798 0.17557 -0.0712 0.0119 1.0000
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Polar data table (+)
Polar graphs
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