EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 432 AIRFOIL (e432-il) Reynolds number: 200,000 Max Cl/Cd: 75.42 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e432-il-200000-n5.txt Download as CSV file: xf-e432-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 432 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0535 0.09033 0.08662 -0.0957 0.8799 0.0171
-11.000 -0.0456 0.08590 0.08211 -0.0985 0.8652 0.0166
-10.750 -0.0424 0.08114 0.07729 -0.1010 0.8514 0.0159
-10.250 -0.1494 0.08051 0.07676 -0.1008 0.8989 0.0142
-10.000 -0.1331 0.07499 0.07116 -0.1080 0.8804 0.0140
-9.750 -0.1283 0.06830 0.06438 -0.1151 0.8604 0.0137
-9.500 -0.1394 0.05887 0.05483 -0.1241 0.8403 0.0133
-9.250 -0.1622 0.05184 0.04758 -0.1285 0.8215 0.0130
-9.000 -0.1882 0.04683 0.04231 -0.1287 0.8051 0.0127
-8.750 -0.2150 0.04286 0.03805 -0.1260 0.7914 0.0125
-8.500 -0.2328 0.03852 0.03328 -0.1234 0.7806 0.0122
-8.250 -0.2457 0.03388 0.02805 -0.1203 0.7708 0.0119
-8.000 -0.2447 0.03039 0.02397 -0.1180 0.7628 0.0117
-7.750 -0.2331 0.02822 0.02142 -0.1164 0.7552 0.0118
-7.500 -0.2173 0.02642 0.01925 -0.1153 0.7490 0.0118
-7.250 -0.1991 0.02497 0.01756 -0.1143 0.7421 0.0120
-7.000 -0.1789 0.02365 0.01596 -0.1134 0.7360 0.0122
-6.750 -0.1575 0.02249 0.01458 -0.1127 0.7302 0.0124
-6.500 -0.1354 0.02140 0.01331 -0.1119 0.7244 0.0128
-6.250 -0.1124 0.02045 0.01216 -0.1113 0.7194 0.0132
-6.000 -0.0894 0.01959 0.01114 -0.1106 0.7146 0.0136
-5.750 -0.0667 0.01881 0.01023 -0.1098 0.7091 0.0143
-5.500 -0.0439 0.01815 0.00950 -0.1092 0.7042 0.0149
-5.250 -0.0200 0.01763 0.00889 -0.1088 0.7002 0.0160
-5.000 0.0036 0.01715 0.00836 -0.1083 0.6953 0.0180
-4.750 0.0277 0.01674 0.00791 -0.1078 0.6906 0.0203
-4.500 0.0520 0.01629 0.00737 -0.1074 0.6864 0.0231
-4.250 0.0767 0.01585 0.00687 -0.1071 0.6825 0.0271
-4.000 0.1011 0.01546 0.00649 -0.1067 0.6781 0.0363
-3.750 0.1259 0.01506 0.00613 -0.1064 0.6739 0.0512
-3.500 0.1510 0.01466 0.00582 -0.1062 0.6701 0.0780
-3.250 0.1762 0.01424 0.00556 -0.1062 0.6665 0.1243
-3.000 0.2002 0.01370 0.00534 -0.1061 0.6622 0.2042
-2.750 0.2239 0.01296 0.00511 -0.1062 0.6583 0.3402
-2.500 0.2450 0.01209 0.00512 -0.1055 0.6547 0.5632
-2.250 0.2685 0.01222 0.00546 -0.1040 0.6515 0.6712
-2.000 0.2943 0.01240 0.00562 -0.1033 0.6475 0.7063
-1.750 0.3209 0.01257 0.00572 -0.1029 0.6436 0.7283
-1.500 0.3475 0.01274 0.00579 -0.1025 0.6399 0.7444
-1.250 0.3732 0.01295 0.00592 -0.1017 0.6366 0.7582
-1.000 0.3973 0.01324 0.00617 -0.1005 0.6332 0.7763
-0.750 0.4189 0.01351 0.00645 -0.0987 0.6293 0.7909
-0.500 0.4435 0.01364 0.00653 -0.0978 0.6256 0.7987
-0.250 0.4703 0.01369 0.00650 -0.0977 0.6220 0.8027
0.000 0.4992 0.01374 0.00643 -0.0981 0.6190 0.8065
0.250 0.5276 0.01378 0.00642 -0.0985 0.6153 0.8104
0.500 0.5537 0.01382 0.00644 -0.0983 0.6113 0.8126
0.750 0.5804 0.01386 0.00644 -0.0982 0.6075 0.8149
1.000 0.6081 0.01391 0.00642 -0.0983 0.6043 0.8175
1.250 0.6362 0.01398 0.00643 -0.0986 0.6012 0.8200
1.500 0.6630 0.01404 0.00650 -0.0987 0.5969 0.8230
1.750 0.6911 0.01411 0.00653 -0.0991 0.5929 0.8261
2.000 0.7184 0.01416 0.00656 -0.0992 0.5895 0.8282
2.250 0.7463 0.01423 0.00657 -0.0994 0.5864 0.8301
2.500 0.7714 0.01432 0.00670 -0.0991 0.5821 0.8324
2.750 0.7973 0.01440 0.00681 -0.0990 0.5779 0.8352
3.000 0.8245 0.01448 0.00688 -0.0991 0.5741 0.8381
3.250 0.8534 0.01457 0.00691 -0.0996 0.5708 0.8408
3.500 0.8793 0.01468 0.00707 -0.0996 0.5663 0.8434
3.750 0.9039 0.01476 0.00721 -0.0991 0.5616 0.8455
4.000 0.9297 0.01484 0.00729 -0.0990 0.5574 0.8479
4.250 0.9562 0.01493 0.00737 -0.0989 0.5534 0.8508
4.500 0.9802 0.01506 0.00758 -0.0985 0.5480 0.8541
4.750 1.0062 0.01516 0.00771 -0.0985 0.5430 0.8573
5.000 1.0332 0.01525 0.00777 -0.0986 0.5388 0.8598
5.250 1.0546 0.01537 0.00801 -0.0976 0.5328 0.8625
5.500 1.0782 0.01548 0.00816 -0.0971 0.5273 0.8655
5.750 1.1035 0.01558 0.00827 -0.0968 0.5224 0.8689
6.000 1.1257 0.01575 0.00853 -0.0961 0.5158 0.8729
6.250 1.1487 0.01585 0.00868 -0.0955 0.5099 0.8763
6.500 1.1700 0.01600 0.00889 -0.0945 0.5039 0.8799
6.750 1.1910 0.01615 0.00911 -0.0935 0.4969 0.8839
7.000 1.2137 0.01630 0.00929 -0.0929 0.4905 0.8881
7.250 1.2323 0.01648 0.00957 -0.0915 0.4828 0.8923
7.500 1.2520 0.01664 0.00975 -0.0902 0.4758 0.8972
7.750 1.2691 0.01686 0.01008 -0.0886 0.4673 0.9033
8.000 1.2844 0.01703 0.01029 -0.0866 0.4596 0.9096
8.250 1.2979 0.01727 0.01062 -0.0843 0.4505 0.9175
8.500 1.3108 0.01753 0.01094 -0.0819 0.4415 0.9266
8.750 1.3235 0.01783 0.01129 -0.0796 0.4317 0.9393
9.000 1.3380 0.01817 0.01172 -0.0779 0.4206 0.9649
9.250 1.3530 0.01864 0.01222 -0.0765 0.4088 1.0000
9.500 1.3665 0.01925 0.01284 -0.0750 0.3964 1.0000
9.750 1.3777 0.01997 0.01357 -0.0733 0.3831 1.0000
10.000 1.3869 0.02082 0.01441 -0.0713 0.3690 1.0000
10.500 1.3997 0.02294 0.01651 -0.0672 0.3388 1.0000
10.750 1.4036 0.02425 0.01780 -0.0651 0.3234 1.0000
11.000 1.4060 0.02573 0.01927 -0.0630 0.3080 1.0000
11.250 1.4074 0.02739 0.02090 -0.0611 0.2927 1.0000
11.500 1.4078 0.02921 0.02270 -0.0592 0.2777 1.0000
11.750 1.4081 0.03114 0.02462 -0.0576 0.2633 1.0000
12.000 1.4078 0.03320 0.02667 -0.0561 0.2490 1.0000
12.250 1.4080 0.03533 0.02880 -0.0547 0.2355 1.0000
12.500 1.4078 0.03757 0.03105 -0.0536 0.2224 1.0000
12.750 1.4076 0.03988 0.03337 -0.0525 0.2100 1.0000
13.000 1.4070 0.04232 0.03580 -0.0516 0.1981 1.0000
13.250 1.4057 0.04491 0.03840 -0.0507 0.1862 1.0000
13.500 1.4046 0.04757 0.04105 -0.0501 0.1754 1.0000
13.750 1.4049 0.05017 0.04368 -0.0495 0.1640 1.0000
14.000 1.4050 0.05287 0.04640 -0.0491 0.1540 1.0000
14.250 1.4037 0.05578 0.04934 -0.0488 0.1441 1.0000
14.500 1.4025 0.05877 0.05234 -0.0486 0.1345 1.0000
14.750 1.4030 0.06163 0.05524 -0.0485 0.1252 1.0000
15.000 1.4019 0.06475 0.05839 -0.0485 0.1169 1.0000
15.250 1.4002 0.06803 0.06169 -0.0487 0.1087 1.0000
15.500 1.4006 0.07109 0.06481 -0.0489 0.1010 1.0000
15.750 1.3983 0.07458 0.06833 -0.0493 0.0941 1.0000
16.000 1.3981 0.07786 0.07167 -0.0497 0.0872 1.0000
16.250 1.3965 0.08139 0.07526 -0.0502 0.0813 1.0000
16.500 1.3951 0.08494 0.07887 -0.0509 0.0753 1.0000
16.750 1.3933 0.08861 0.08260 -0.0516 0.0702 1.0000
17.000 1.3915 0.09234 0.08640 -0.0524 0.0651 1.0000
17.250 1.3890 0.09622 0.09034 -0.0534 0.0608 1.0000
17.500 1.3872 0.10006 0.09426 -0.0545 0.0564 1.0000
17.750 1.3829 0.10430 0.09856 -0.0558 0.0528 1.0000
18.000 1.3821 0.10805 0.10242 -0.0569 0.0490 1.0000
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Polar data table (+)
Polar graphs
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