GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 200,000 Max Cl/Cd: 81.91 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe529-il-200000-n5.txt Download as CSV file: xf-goe529-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2432 0.11241 0.10894 -0.0376 1.0000 0.0240
-9.750 -0.2409 0.11008 0.10665 -0.0382 1.0000 0.0263
-9.500 -0.2422 0.10789 0.10453 -0.0390 1.0000 0.0271
-9.000 -0.2305 0.09867 0.09535 -0.0434 0.9890 0.0207
-8.750 -0.2163 0.09455 0.09124 -0.0472 0.9795 0.0206
-8.500 -0.2007 0.09049 0.08717 -0.0514 0.9692 0.0204
-8.250 -0.1872 0.08526 0.08193 -0.0582 0.9560 0.0209
-8.000 -0.1628 0.08314 0.07980 -0.0608 0.9453 0.0231
-7.750 -0.1424 0.07922 0.07585 -0.0663 0.9297 0.0243
-7.500 -0.1247 0.07473 0.07131 -0.0723 0.9101 0.0242
-7.250 -0.1083 0.07038 0.06689 -0.0782 0.8898 0.0242
-7.000 -0.0938 0.06628 0.06271 -0.0834 0.8693 0.0246
-6.750 -0.0801 0.06232 0.05866 -0.0881 0.8499 0.0256
-6.500 -0.0669 0.05717 0.05336 -0.0942 0.8318 0.0268
-6.250 -0.0519 0.05204 0.04806 -0.0990 0.8158 0.0272
-6.000 -0.0347 0.04552 0.04131 -0.1046 0.8014 0.0280
-5.750 -0.0171 0.04430 0.03999 -0.1049 0.7877 0.0292
-5.500 0.0032 0.04289 0.03845 -0.1055 0.7738 0.0307
-5.250 0.0245 0.03916 0.03448 -0.1078 0.7601 0.0320
-5.000 0.0466 0.03428 0.02924 -0.1101 0.7475 0.0328
-4.750 0.0688 0.02796 0.02229 -0.1119 0.7365 0.0353
-4.500 0.0906 0.02350 0.01709 -0.1123 0.7258 0.0362
-4.250 0.1138 0.02100 0.01404 -0.1121 0.7160 0.0373
-4.000 0.1384 0.01992 0.01274 -0.1119 0.7073 0.0387
-3.750 0.1638 0.01883 0.01137 -0.1116 0.6988 0.0396
-3.500 0.1897 0.01780 0.01004 -0.1113 0.6917 0.0404
-3.250 0.2159 0.01693 0.00890 -0.1109 0.6842 0.0412
-3.000 0.2423 0.01622 0.00795 -0.1106 0.6778 0.0422
-2.750 0.2690 0.01567 0.00722 -0.1103 0.6710 0.0436
-2.500 0.2956 0.01521 0.00657 -0.1099 0.6651 0.0452
-2.250 0.3223 0.01473 0.00595 -0.1096 0.6591 0.0461
-2.000 0.3490 0.01432 0.00542 -0.1093 0.6531 0.0470
-1.750 0.3754 0.01392 0.00493 -0.1089 0.6478 0.0481
-1.500 0.4018 0.01360 0.00460 -0.1086 0.6418 0.0500
-1.250 0.4284 0.01341 0.00436 -0.1083 0.6365 0.0524
-1.000 0.4552 0.01325 0.00414 -0.1080 0.6313 0.0554
-0.750 0.4818 0.01309 0.00396 -0.1076 0.6253 0.0602
-0.500 0.5084 0.01300 0.00385 -0.1073 0.6200 0.0705
-0.250 0.5350 0.01288 0.00375 -0.1071 0.6146 0.0863
0.000 0.5615 0.01278 0.00371 -0.1068 0.6087 0.1052
0.250 0.5881 0.01276 0.00368 -0.1065 0.6033 0.1257
0.500 0.6144 0.01270 0.00370 -0.1062 0.5971 0.1516
1.000 0.6657 0.01238 0.00377 -0.1055 0.5855 0.2934
1.250 0.7085 0.01096 0.00385 -0.1087 0.5781 1.0000
1.500 0.7343 0.01109 0.00384 -0.1082 0.5721 1.0000
1.750 0.7600 0.01119 0.00390 -0.1077 0.5643 1.0000
2.000 0.7856 0.01132 0.00392 -0.1072 0.5573 1.0000
2.250 0.8110 0.01142 0.00399 -0.1067 0.5484 1.0000
2.500 0.8362 0.01154 0.00403 -0.1061 0.5399 1.0000
2.750 0.8614 0.01165 0.00410 -0.1055 0.5303 1.0000
3.000 0.8866 0.01178 0.00419 -0.1050 0.5209 1.0000
3.250 0.9114 0.01192 0.00427 -0.1044 0.5108 1.0000
3.500 0.9360 0.01206 0.00436 -0.1038 0.4996 1.0000
3.750 0.9605 0.01222 0.00447 -0.1031 0.4878 1.0000
4.000 0.9848 0.01240 0.00461 -0.1025 0.4772 1.0000
4.250 1.0089 0.01260 0.00476 -0.1018 0.4673 1.0000
4.500 1.0331 0.01281 0.00494 -0.1012 0.4574 1.0000
4.750 1.0572 0.01304 0.00516 -0.1005 0.4485 1.0000
5.000 1.0809 0.01330 0.00537 -0.0998 0.4398 1.0000
5.250 1.1050 0.01354 0.00562 -0.0992 0.4315 1.0000
5.500 1.1284 0.01382 0.00589 -0.0985 0.4242 1.0000
5.750 1.1525 0.01407 0.00618 -0.0979 0.4167 1.0000
6.000 1.1757 0.01437 0.00647 -0.0971 0.4097 1.0000
6.250 1.1992 0.01464 0.00679 -0.0965 0.4020 1.0000
6.500 1.2217 0.01497 0.00713 -0.0957 0.3942 1.0000
6.750 1.2446 0.01525 0.00748 -0.0949 0.3856 1.0000
7.000 1.2663 0.01559 0.00784 -0.0940 0.3769 1.0000
7.250 1.2873 0.01594 0.00821 -0.0929 0.3652 1.0000
7.500 1.3066 0.01632 0.00861 -0.0916 0.3501 1.0000
7.750 1.3245 0.01674 0.00902 -0.0901 0.3311 1.0000
8.000 1.3420 0.01720 0.00947 -0.0885 0.3133 1.0000
8.250 1.3581 0.01771 0.00996 -0.0867 0.2951 1.0000
8.500 1.3718 0.01832 0.01052 -0.0847 0.2762 1.0000
8.750 1.3831 0.01900 0.01117 -0.0822 0.2539 1.0000
9.000 1.3895 0.01984 0.01191 -0.0790 0.2311 1.0000
9.500 1.3915 0.02229 0.01401 -0.0719 0.1577 1.0000
9.750 1.3840 0.02420 0.01565 -0.0678 0.1239 1.0000
10.000 1.3828 0.02589 0.01726 -0.0648 0.1070 1.0000
10.250 1.3850 0.02746 0.01882 -0.0624 0.0788 1.0000
10.500 1.3710 0.03037 0.02145 -0.0592 0.0472 1.0000
11.000 1.3622 0.03531 0.02637 -0.0553 0.0218 1.0000
11.250 1.3621 0.03764 0.02877 -0.0540 0.0195 1.0000
11.500 1.3634 0.03994 0.03117 -0.0529 0.0181 1.0000
11.750 1.3645 0.04235 0.03373 -0.0520 0.0170 1.0000
12.000 1.3645 0.04496 0.03648 -0.0513 0.0160 1.0000
12.250 1.3629 0.04783 0.03949 -0.0507 0.0152 1.0000
12.500 1.3609 0.05084 0.04263 -0.0503 0.0147 1.0000
12.750 1.3565 0.05422 0.04615 -0.0500 0.0142 1.0000
13.000 1.3496 0.05802 0.05010 -0.0499 0.0137 1.0000
13.250 1.3421 0.06203 0.05426 -0.0501 0.0134 1.0000
13.500 1.3369 0.06589 0.05825 -0.0504 0.0132 1.0000
13.750 1.3332 0.06966 0.06215 -0.0508 0.0130 1.0000
14.000 1.3290 0.07359 0.06624 -0.0513 0.0127 1.0000
14.250 1.3247 0.07763 0.07041 -0.0520 0.0124 1.0000
14.500 1.3213 0.08164 0.07455 -0.0527 0.0120 1.0000
14.750 1.3175 0.08578 0.07881 -0.0536 0.0117 1.0000
15.000 1.3141 0.08990 0.08304 -0.0546 0.0114 1.0000
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Polar data table (+)
Polar graphs
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