GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 50,000 Max Cl/Cd: 23.6 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe329-il-50000.txt Download as CSV file: xf-goe329-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2789 0.11430 0.10772 -0.0337 1.0000 0.1353
-8.500 -0.2975 0.11495 0.10855 -0.0329 1.0000 0.1368
-8.250 -0.3205 0.11574 0.10952 -0.0307 1.0000 0.1372
-8.000 -0.2873 0.10768 0.10140 -0.0293 1.0000 0.1443
-7.750 -0.2981 0.10664 0.10048 -0.0268 1.0000 0.1477
-7.500 -0.3167 0.10639 0.10037 -0.0238 1.0000 0.1501
-7.250 -0.3372 0.10647 0.10059 -0.0221 1.0000 0.1519
-7.000 -0.3570 0.10690 0.10114 -0.0230 1.0000 0.1531
-6.750 -0.3509 0.10224 0.09654 -0.0192 1.0000 0.1563
-6.500 -0.3509 0.09972 0.09406 -0.0167 1.0000 0.1612
-6.250 -0.3590 0.09840 0.09281 -0.0167 1.0000 0.1662
-6.000 -0.3694 0.09862 0.09309 -0.0230 1.0000 0.1695
-5.750 -0.3647 0.09375 0.08829 -0.0160 1.0000 0.1738
-5.500 -0.3647 0.09169 0.08627 -0.0158 1.0000 0.1809
-5.250 -0.3639 0.08962 0.08423 -0.0193 1.0000 0.1867
-5.000 -0.3614 0.08676 0.08143 -0.0160 1.0000 0.1936
-4.750 -0.3561 0.08446 0.07914 -0.0192 1.0000 0.2031
-4.500 -0.3467 0.08266 0.07729 -0.0227 1.0000 0.2170
-4.250 -0.3458 0.07948 0.07423 -0.0180 1.0000 0.2255
-4.000 -0.3382 0.07701 0.07176 -0.0187 1.0000 0.2393
-3.750 -0.3241 0.07529 0.06997 -0.0228 1.0000 0.2628
-3.500 -0.3156 0.07264 0.06737 -0.0229 1.0000 0.2807
-3.000 -0.2755 0.06669 0.06151 -0.0240 0.9884 0.3490
-2.750 -0.2515 0.06373 0.05863 -0.0228 0.9761 0.4161
-2.500 -0.2364 0.06139 0.05639 -0.0187 0.9634 0.5051
-2.250 -0.2292 0.05858 0.05373 -0.0104 0.9514 0.5726
-2.000 -0.2197 0.05615 0.05140 -0.0020 0.9397 0.6455
-1.750 -0.2059 0.05374 0.04905 0.0047 0.9272 0.7114
-1.500 -0.1848 0.05133 0.04667 0.0078 0.9132 0.7600
-1.250 -0.1465 0.04883 0.04413 0.0021 0.8974 0.7793
-1.000 0.2407 0.04455 0.03621 -0.1049 0.8695 0.2451
-0.750 0.2958 0.04302 0.03412 -0.1092 0.8551 0.2087
-0.500 0.3488 0.04191 0.03237 -0.1126 0.8408 0.1831
-0.250 0.4018 0.04061 0.03058 -0.1158 0.8281 0.1682
0.000 0.4549 0.03899 0.02870 -0.1191 0.8166 0.1608
0.250 0.4922 0.03829 0.02768 -0.1196 0.8018 0.1562
0.500 0.5272 0.03767 0.02687 -0.1198 0.7873 0.1575
0.750 0.5598 0.03720 0.02627 -0.1197 0.7731 0.1618
1.000 0.5913 0.03682 0.02577 -0.1194 0.7595 0.1653
1.250 0.6238 0.03640 0.02525 -0.1192 0.7469 0.1699
1.500 0.6658 0.03531 0.02411 -0.1200 0.7378 0.1827
1.750 0.6908 0.03538 0.02427 -0.1194 0.7239 0.2047
2.000 0.7071 0.03394 0.02472 -0.1172 0.7111 1.0000
2.250 0.7330 0.03458 0.02486 -0.1161 0.6991 1.0000
2.500 0.7728 0.03415 0.02398 -0.1162 0.6914 1.0000
2.750 0.7902 0.03535 0.02499 -0.1151 0.6782 1.0000
3.000 0.8079 0.03661 0.02612 -0.1142 0.6662 1.0000
3.250 0.8492 0.03598 0.02527 -0.1146 0.6601 1.0000
3.500 0.8587 0.03800 0.02726 -0.1134 0.6475 1.0000
3.750 0.8707 0.03991 0.02913 -0.1123 0.6365 1.0000
4.000 0.9077 0.03964 0.02875 -0.1125 0.6302 1.0000
4.250 0.9061 0.04292 0.03208 -0.1111 0.6188 1.0000
4.500 0.9481 0.04226 0.03132 -0.1115 0.6139 1.0000
4.750 0.9322 0.04695 0.03611 -0.1096 0.6020 1.0000
5.000 0.9274 0.05082 0.04001 -0.1084 0.5933 1.0000
5.250 0.9292 0.05409 0.04329 -0.1075 0.5860 1.0000
5.500 0.9082 0.05965 0.04889 -0.1063 0.5787 1.0000
5.750 0.8944 0.06449 0.05375 -0.1055 0.5725 1.0000
6.000 0.9255 0.06534 0.05464 -0.1056 0.5682 1.0000
6.250 0.8990 0.07162 0.06094 -0.1050 0.5650 1.0000
6.500 0.8797 0.07704 0.06638 -0.1047 0.5632 1.0000
6.750 0.8718 0.08159 0.07099 -0.1047 0.5632 1.0000
7.000 0.8734 0.08569 0.07513 -0.1052 0.5652 1.0000
7.250 0.8814 0.08947 0.07897 -0.1060 0.5676 1.0000
7.500 0.7410 0.10508 0.09480 -0.1099 0.6948 1.0000
7.750 0.7683 0.10889 0.09862 -0.1118 0.6905 1.0000
8.000 0.7630 0.11020 0.09996 -0.1097 0.6795 1.0000
8.250 0.7792 0.11337 0.10316 -0.1103 0.6735 1.0000
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Polar data table (+)
Polar graphs
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