GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 500,000 Max Cl/Cd: 96.5 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe421-il-500000.txt Download as CSV file: xf-goe421-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.2807 0.06056 0.05729 -0.1723 0.9453 0.0389
-14.250 -0.3304 0.05076 0.04721 -0.1797 0.9379 0.0390
-14.000 -0.3575 0.04456 0.04084 -0.1844 0.9280 0.0392
-13.750 -0.3735 0.03912 0.03520 -0.1895 0.9203 0.0396
-13.500 -0.3819 0.03409 0.02994 -0.1955 0.9108 0.0399
-13.250 -0.3872 0.03010 0.02570 -0.2011 0.9016 0.0402
-13.000 -0.3826 0.02811 0.02363 -0.2012 0.8948 0.0408
-12.750 -0.3664 0.02693 0.02239 -0.2017 0.8898 0.0415
-12.500 -0.3515 0.02603 0.02145 -0.2015 0.8826 0.0421
-12.250 -0.3324 0.02508 0.02038 -0.2018 0.8774 0.0429
-12.000 -0.3142 0.02415 0.01932 -0.2019 0.8717 0.0438
-11.750 -0.2961 0.02327 0.01830 -0.2017 0.8653 0.0446
-11.500 -0.2739 0.02245 0.01727 -0.2019 0.8604 0.0454
-11.250 -0.2564 0.02129 0.01602 -0.2014 0.8543 0.0463
-11.000 -0.2348 0.02062 0.01534 -0.2011 0.8482 0.0472
-10.750 -0.2092 0.02008 0.01471 -0.2014 0.8433 0.0482
-10.500 -0.1871 0.01956 0.01411 -0.2010 0.8375 0.0492
-10.250 -0.1641 0.01900 0.01344 -0.2008 0.8318 0.0502
-10.000 -0.1377 0.01852 0.01279 -0.2010 0.8270 0.0512
-9.750 -0.1163 0.01775 0.01195 -0.2005 0.8214 0.0523
-9.500 -0.0933 0.01720 0.01139 -0.2001 0.8156 0.0535
-9.250 -0.0668 0.01678 0.01089 -0.2002 0.8106 0.0547
-9.000 -0.0420 0.01640 0.01044 -0.2000 0.8055 0.0560
-8.750 -0.0175 0.01605 0.01000 -0.1996 0.8000 0.0573
-8.500 0.0088 0.01567 0.00950 -0.1996 0.7952 0.0585
-8.250 0.0340 0.01509 0.00889 -0.1996 0.7905 0.0603
-8.000 0.0578 0.01477 0.00855 -0.1990 0.7850 0.0618
-7.750 0.0837 0.01447 0.00819 -0.1988 0.7798 0.0635
-7.500 0.1123 0.01424 0.00783 -0.1991 0.7753 0.0653
-7.250 0.1359 0.01379 0.00738 -0.1986 0.7704 0.0675
-7.000 0.1611 0.01351 0.00709 -0.1983 0.7654 0.0697
-6.750 0.1884 0.01329 0.00679 -0.1983 0.7608 0.0722
-6.500 0.2167 0.01309 0.00648 -0.1985 0.7564 0.0746
-6.250 0.2405 0.01275 0.00617 -0.1979 0.7513 0.0779
-6.000 0.2669 0.01257 0.00595 -0.1977 0.7466 0.0815
-5.750 0.2948 0.01233 0.00565 -0.1979 0.7424 0.0859
-5.500 0.3221 0.01214 0.00544 -0.1979 0.7380 0.0911
-5.250 0.3470 0.01190 0.00521 -0.1975 0.7331 0.0974
-5.000 0.3733 0.01170 0.00498 -0.1973 0.7281 0.1063
-4.750 0.4019 0.01144 0.00473 -0.1976 0.7234 0.1222
-4.500 0.4261 0.01125 0.00469 -0.1970 0.7181 0.1497
-4.250 0.4523 0.01129 0.00474 -0.1967 0.7127 0.1732
-4.000 0.4809 0.01139 0.00479 -0.1968 0.7079 0.1856
-3.750 0.5085 0.01146 0.00481 -0.1968 0.7033 0.1936
-3.500 0.5335 0.01151 0.00487 -0.1962 0.6981 0.2003
-3.250 0.5601 0.01161 0.00488 -0.1959 0.6928 0.2059
-3.000 0.5886 0.01159 0.00480 -0.1962 0.6877 0.2115
-2.750 0.6116 0.01158 0.00482 -0.1952 0.6822 0.2161
-2.500 0.6368 0.01161 0.00481 -0.1947 0.6767 0.2208
-2.250 0.6649 0.01170 0.00479 -0.1948 0.6721 0.2242
-2.000 0.6904 0.01163 0.00473 -0.1944 0.6679 0.2284
-1.750 0.7149 0.01159 0.00472 -0.1939 0.6634 0.2325
-1.500 0.7406 0.01162 0.00472 -0.1935 0.6589 0.2366
-1.250 0.7684 0.01170 0.00472 -0.1936 0.6546 0.2412
-1.000 0.7927 0.01173 0.00474 -0.1930 0.6501 0.2447
-0.750 0.8160 0.01166 0.00471 -0.1922 0.6453 0.2495
-0.500 0.8410 0.01167 0.00472 -0.1918 0.6406 0.2535
-0.250 0.8690 0.01174 0.00472 -0.1919 0.6363 0.2572
0.000 0.8903 0.01175 0.00475 -0.1907 0.6319 0.2595
0.250 0.9117 0.01178 0.00478 -0.1895 0.6271 0.2618
0.500 0.9353 0.01180 0.00477 -0.1888 0.6224 0.2648
0.750 0.9607 0.01184 0.00480 -0.1885 0.6179 0.2686
1.000 0.9808 0.01188 0.00489 -0.1871 0.6130 0.2723
1.250 1.0032 0.01195 0.00497 -0.1862 0.6078 0.2764
1.500 1.0277 0.01207 0.00503 -0.1857 0.6029 0.2810
1.750 1.0503 0.01215 0.00518 -0.1849 0.5978 0.2879
2.000 1.0722 0.01225 0.00533 -0.1839 0.5920 0.2972
2.250 1.0949 0.01238 0.00547 -0.1831 0.5863 0.3121
2.500 1.1165 0.01250 0.00568 -0.1822 0.5805 0.3378
2.750 1.1374 0.01263 0.00590 -0.1812 0.5737 0.3735
3.250 1.1787 0.01295 0.00637 -0.1790 0.5602 0.4379
3.500 1.1984 0.01314 0.00662 -0.1778 0.5527 0.4728
3.750 1.2187 0.01327 0.00693 -0.1768 0.5453 0.5349
4.000 1.2304 0.01275 0.00732 -0.1738 0.5372 1.0000
4.250 1.2485 0.01310 0.00762 -0.1723 0.5286 1.0000
4.500 1.2651 0.01351 0.00798 -0.1706 0.5185 1.0000
4.750 1.2817 0.01395 0.00837 -0.1689 0.5080 1.0000
5.000 1.2960 0.01448 0.00883 -0.1669 0.4966 1.0000
5.250 1.3092 0.01509 0.00937 -0.1648 0.4836 1.0000
5.500 1.3227 0.01572 0.00994 -0.1628 0.4702 1.0000
5.750 1.3341 0.01647 0.01062 -0.1605 0.4565 1.0000
6.000 1.3448 0.01729 0.01136 -0.1582 0.4431 1.0000
6.250 1.3537 0.01824 0.01221 -0.1557 0.4301 1.0000
6.500 1.3654 0.01909 0.01300 -0.1536 0.4179 1.0000
6.750 1.3767 0.01998 0.01385 -0.1516 0.4075 1.0000
7.000 1.3865 0.02100 0.01479 -0.1495 0.3980 1.0000
7.250 1.4008 0.02181 0.01559 -0.1480 0.3901 1.0000
7.500 1.4126 0.02276 0.01649 -0.1462 0.3830 1.0000
7.750 1.4261 0.02365 0.01736 -0.1448 0.3771 1.0000
8.000 1.4416 0.02443 0.01814 -0.1436 0.3720 1.0000
8.250 1.4547 0.02537 0.01904 -0.1421 0.3671 1.0000
8.500 1.4671 0.02636 0.02000 -0.1406 0.3627 1.0000
8.750 1.4849 0.02705 0.02073 -0.1398 0.3595 1.0000
9.000 1.5007 0.02785 0.02155 -0.1388 0.3560 1.0000
9.250 1.5153 0.02874 0.02244 -0.1376 0.3526 1.0000
9.500 1.5290 0.02967 0.02336 -0.1364 0.3493 1.0000
9.750 1.5432 0.03057 0.02422 -0.1352 0.3460 1.0000
10.000 1.5594 0.03141 0.02512 -0.1344 0.3435 1.0000
10.250 1.5748 0.03229 0.02606 -0.1335 0.3402 1.0000
10.500 1.5887 0.03328 0.02707 -0.1324 0.3366 1.0000
10.750 1.6007 0.03440 0.02817 -0.1312 0.3330 1.0000
11.000 1.6136 0.03539 0.02912 -0.1300 0.3290 1.0000
11.250 1.6281 0.03641 0.03023 -0.1292 0.3265 1.0000
11.500 1.6419 0.03747 0.03135 -0.1283 0.3236 1.0000
11.750 1.6557 0.03851 0.03243 -0.1274 0.3207 1.0000
12.000 1.6679 0.03967 0.03360 -0.1264 0.3176 1.0000
12.250 1.6784 0.04094 0.03486 -0.1252 0.3139 1.0000
12.500 1.6913 0.04206 0.03603 -0.1243 0.3109 1.0000
12.750 1.7038 0.04329 0.03734 -0.1235 0.3080 1.0000
13.000 1.7152 0.04461 0.03872 -0.1226 0.3047 1.0000
13.250 1.7252 0.04601 0.04015 -0.1216 0.3010 1.0000
13.500 1.7323 0.04764 0.04176 -0.1203 0.2967 1.0000
13.750 1.7427 0.04912 0.04333 -0.1195 0.2930 1.0000
14.000 1.7522 0.05069 0.04499 -0.1187 0.2885 1.0000
14.250 1.7582 0.05255 0.04687 -0.1176 0.2835 1.0000
14.500 1.7635 0.05446 0.04879 -0.1165 0.2789 1.0000
14.750 1.7727 0.05611 0.05054 -0.1158 0.2738 1.0000
15.000 1.7767 0.05824 0.05270 -0.1148 0.2673 1.0000
15.250 1.7802 0.06044 0.05494 -0.1137 0.2605 1.0000
15.500 1.7796 0.06310 0.05763 -0.1126 0.2505 1.0000
15.750 1.7771 0.06598 0.06051 -0.1114 0.2366 1.0000
16.000 1.7602 0.07039 0.06483 -0.1096 0.2119 1.0000
16.250 1.7228 0.07708 0.07134 -0.1070 0.1799 1.0000
16.500 1.6954 0.08284 0.07702 -0.1052 0.1635 1.0000
16.750 1.6777 0.08761 0.08179 -0.1039 0.1536 1.0000
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