GOE 464 AIRFOIL (goe464-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 464 AIRFOIL (goe464-il) Reynolds number: 500,000 Max Cl/Cd: 97.05 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe464-il-500000-n5.txt Download as CSV file: xf-goe464-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 464 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0809 0.08905 0.08606 -0.0877 0.8301 0.0143
-8.500 0.0894 0.08681 0.08379 -0.0883 0.8225 0.0143
-8.250 0.0985 0.08473 0.08170 -0.0887 0.8158 0.0143
-7.750 0.1099 0.07959 0.07653 -0.0890 0.8018 0.0113
-7.250 0.1228 0.07496 0.07189 -0.0901 0.7870 0.0114
-7.000 0.1374 0.07398 0.07092 -0.0903 0.7785 0.0119
-6.750 0.1474 0.07107 0.06797 -0.0921 0.7693 0.0116
-6.500 0.1617 0.06934 0.06624 -0.0932 0.7581 0.0118
-6.250 0.1761 0.06728 0.06415 -0.0946 0.7462 0.0120
-6.000 0.1916 0.06556 0.06237 -0.0959 0.7280 0.0127
-5.750 0.2069 0.06328 0.06000 -0.0976 0.7034 0.0131
-5.500 0.2229 0.06091 0.05750 -0.0996 0.6761 0.0135
-5.250 0.2412 0.05806 0.05451 -0.1024 0.6554 0.0139
-5.000 0.2642 0.05418 0.05052 -0.1072 0.6413 0.0145
-4.750 0.2861 0.05253 0.04879 -0.1091 0.6291 0.0147
-4.500 0.3091 0.05101 0.04720 -0.1110 0.6192 0.0152
-4.250 0.3351 0.04890 0.04501 -0.1140 0.6109 0.0165
-4.000 0.3712 0.04418 0.04017 -0.1212 0.6034 0.0178
-3.750 0.3971 0.04297 0.03890 -0.1229 0.5957 0.0183
-3.250 0.4681 0.03680 0.03251 -0.1329 0.5818 0.0216
-2.750 0.5500 0.02921 0.02456 -0.1447 0.5683 0.0258
-2.500 0.6044 0.02156 0.01629 -0.1551 0.5620 0.0289
-2.250 0.6359 0.01976 0.01426 -0.1568 0.5541 0.0296
-2.000 0.6642 0.01895 0.01329 -0.1572 0.5458 0.0301
-1.750 0.6909 0.01897 0.01330 -0.1568 0.5378 0.0310
-1.500 0.7175 0.01882 0.01309 -0.1565 0.5286 0.0320
-1.250 0.7446 0.01855 0.01275 -0.1564 0.5189 0.0327
-1.000 0.7713 0.01829 0.01239 -0.1561 0.5080 0.0334
-0.750 0.7980 0.01804 0.01204 -0.1559 0.4961 0.0340
-0.500 0.8246 0.01780 0.01172 -0.1557 0.4854 0.0347
-0.250 0.8507 0.01767 0.01151 -0.1553 0.4747 0.0356
0.000 0.8771 0.01753 0.01132 -0.1550 0.4641 0.0374
0.250 0.9033 0.01734 0.01107 -0.1546 0.4540 0.0398
0.500 0.9281 0.01754 0.01128 -0.1540 0.4431 0.0433
0.750 0.9521 0.01797 0.01175 -0.1533 0.4333 0.0486
1.250 1.0073 0.01686 0.01031 -0.1531 0.4175 0.0656
1.500 1.0329 0.01684 0.01022 -0.1526 0.4098 0.0679
1.750 1.0598 0.01654 0.00980 -0.1523 0.4033 0.0708
2.000 1.0840 0.01682 0.01010 -0.1517 0.3958 0.0725
2.250 1.1091 0.01674 0.00993 -0.1512 0.3886 0.0736
2.500 1.1352 0.01653 0.00965 -0.1508 0.3810 0.0747
3.000 1.1858 0.01633 0.00927 -0.1498 0.3642 0.0776
3.250 1.2092 0.01654 0.00946 -0.1491 0.3556 0.0803
3.500 1.2350 0.01639 0.00925 -0.1486 0.3495 0.0813
3.750 1.2602 0.01624 0.00902 -0.1481 0.3432 0.0813
4.000 1.2847 0.01614 0.00884 -0.1474 0.3372 0.0813
4.250 1.3101 0.01599 0.00865 -0.1469 0.3317 0.0814
4.500 1.3347 0.01591 0.00850 -0.1462 0.3256 0.0816
4.750 1.3588 0.01587 0.00838 -0.1455 0.3202 0.0819
5.000 1.3839 0.01575 0.00821 -0.1449 0.3154 0.0822
5.500 1.4314 0.01577 0.00818 -0.1434 0.3055 0.0837
5.750 1.4550 0.01582 0.00822 -0.1426 0.3011 0.0840
6.000 1.4786 0.01585 0.00825 -0.1419 0.2961 0.0843
6.250 1.5012 0.01595 0.00834 -0.1410 0.2901 0.0847
6.500 1.5237 0.01607 0.00843 -0.1401 0.2846 0.0853
6.750 1.5464 0.01616 0.00852 -0.1392 0.2784 0.0859
7.000 1.5678 0.01632 0.00865 -0.1381 0.2725 0.0866
7.250 1.5896 0.01645 0.00879 -0.1370 0.2673 0.0872
7.500 1.6110 0.01660 0.00893 -0.1359 0.2609 0.0883
7.750 1.6305 0.01686 0.00914 -0.1345 0.2545 0.0897
8.000 1.6509 0.01705 0.00939 -0.1333 0.2475 0.0902
8.250 1.6677 0.01739 0.00971 -0.1315 0.2389 0.0907
8.500 1.6837 0.01770 0.01002 -0.1296 0.2285 0.0912
8.750 1.6983 0.01808 0.01039 -0.1274 0.2200 0.0918
9.000 1.7127 0.01852 0.01081 -0.1253 0.2102 0.0924
9.250 1.7265 0.01901 0.01130 -0.1231 0.2011 0.0931
9.500 1.7383 0.01961 0.01187 -0.1207 0.1917 0.0937
9.750 1.7506 0.02020 0.01245 -0.1185 0.1826 0.0943
10.000 1.7614 0.02091 0.01314 -0.1161 0.1748 0.0952
10.250 1.7720 0.02165 0.01387 -0.1139 0.1668 0.0963
10.500 1.7808 0.02251 0.01474 -0.1115 0.1585 0.0968
10.750 1.7895 0.02343 0.01567 -0.1093 0.1506 0.0975
11.000 1.7982 0.02438 0.01664 -0.1071 0.1440 0.0980
11.250 1.8079 0.02531 0.01761 -0.1052 0.1383 0.0986
11.500 1.8149 0.02649 0.01880 -0.1032 0.1327 0.0992
11.750 1.8246 0.02752 0.01989 -0.1015 0.1276 0.1000
12.000 1.8315 0.02880 0.02119 -0.0996 0.1215 0.1007
12.250 1.8369 0.03025 0.02267 -0.0978 0.1155 0.1012
12.500 1.8425 0.03173 0.02418 -0.0961 0.1091 0.1018
12.750 1.8448 0.03356 0.02601 -0.0943 0.1022 0.1023
13.000 1.8472 0.03544 0.02793 -0.0927 0.0947 0.1027
13.250 1.8469 0.03766 0.03017 -0.0911 0.0868 0.1034
13.500 1.8405 0.04059 0.03308 -0.0895 0.0757 0.1041
13.750 1.8324 0.04387 0.03636 -0.0882 0.0662 0.1048
14.250 1.8141 0.05140 0.04394 -0.0867 0.0509 0.1062
14.500 1.8053 0.05544 0.04804 -0.0865 0.0446 0.1068
14.750 1.7885 0.06071 0.05333 -0.0866 0.0339 0.1068
15.000 1.7660 0.06702 0.05965 -0.0872 0.0208 0.1068
15.250 1.7483 0.07295 0.06566 -0.0880 0.0165 0.1070
15.500 1.7375 0.07801 0.07084 -0.0889 0.0146 0.1074
15.750 1.7287 0.08290 0.07585 -0.0899 0.0133 0.1077
16.000 1.7197 0.08798 0.08106 -0.0911 0.0124 0.1080
16.250 1.7097 0.09331 0.08652 -0.0925 0.0116 0.1083
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