EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 432 AIRFOIL (e432-il) Reynolds number: 200,000 Max Cl/Cd: 75.4 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e432-il-200000.txt Download as CSV file: xf-e432-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1599 0.09714 0.09391 -0.0816 0.9599 0.0474
-9.750 -0.1478 0.09189 0.08865 -0.0880 0.9489 0.0497
-9.500 -0.1629 0.07910 0.07580 -0.1121 0.9343 0.0516
-9.250 -0.1239 0.07814 0.07488 -0.1064 0.9306 0.0530
-9.000 -0.0973 0.07460 0.07128 -0.1104 0.9194 0.0547
-8.750 -0.0800 0.06879 0.06540 -0.1191 0.9049 0.0573
-8.500 -0.0889 0.06103 0.05744 -0.1306 0.8832 0.0594
-8.250 -0.1352 0.05817 0.05415 -0.1309 0.8583 0.0608
-8.000 -0.1562 0.05691 0.05241 -0.1289 0.8435 0.0612
-7.750 -0.1320 0.05088 0.04664 -0.1302 0.8361 0.0629
-7.500 -0.1209 0.04873 0.04444 -0.1295 0.8265 0.0644
-7.250 -0.1131 0.04659 0.04215 -0.1287 0.8181 0.0668
-7.000 -0.1264 0.04459 0.03949 -0.1262 0.8082 0.0732
-6.750 -0.1077 0.04142 0.03639 -0.1262 0.8019 0.0749
-6.500 -0.1102 0.03126 0.02496 -0.1217 0.7955 0.0377
-6.250 -0.0938 0.02721 0.02015 -0.1193 0.7889 0.0301
-6.000 -0.0708 0.02508 0.01772 -0.1187 0.7838 0.0292
-5.750 -0.0492 0.02335 0.01571 -0.1176 0.7775 0.0288
-5.500 -0.0246 0.02187 0.01397 -0.1169 0.7719 0.0288
-5.250 0.0022 0.02065 0.01249 -0.1164 0.7673 0.0296
-5.000 0.0260 0.01982 0.01151 -0.1154 0.7614 0.0307
-4.750 0.0493 0.01883 0.01059 -0.1148 0.7561 0.0332
-4.500 0.0747 0.01816 0.00984 -0.1144 0.7518 0.0377
-4.250 0.0975 0.01759 0.00929 -0.1136 0.7468 0.0426
-4.000 0.1188 0.01685 0.00860 -0.1126 0.7413 0.0526
-3.750 0.1418 0.01608 0.00794 -0.1121 0.7369 0.0767
-3.500 0.1651 0.01520 0.00738 -0.1118 0.7332 0.1473
-3.250 0.1806 0.01377 0.00707 -0.1111 0.7279 0.3848
-3.000 0.1952 0.01332 0.00773 -0.1080 0.7232 0.6764
-2.750 0.2204 0.01381 0.00812 -0.1065 0.7193 0.7287
-2.500 0.2430 0.01438 0.00862 -0.1044 0.7154 0.7540
-2.250 0.2631 0.01487 0.00908 -0.1020 0.7105 0.7743
-2.000 0.2839 0.01531 0.00943 -0.0996 0.7061 0.7910
-1.750 0.3059 0.01566 0.00969 -0.0974 0.7025 0.8046
-1.500 0.3267 0.01598 0.00994 -0.0952 0.6987 0.8168
-1.250 0.3455 0.01623 0.01015 -0.0930 0.6940 0.8293
-1.000 0.3651 0.01646 0.01032 -0.0906 0.6897 0.8433
-0.750 0.3837 0.01669 0.01048 -0.0876 0.6863 0.8588
-0.500 0.4026 0.01687 0.01059 -0.0847 0.6829 0.8712
-0.250 0.4198 0.01692 0.01066 -0.0824 0.6781 0.8798
0.000 0.4431 0.01692 0.01059 -0.0817 0.6738 0.8866
0.250 0.4699 0.01686 0.01043 -0.0817 0.6703 0.8914
0.500 0.4983 0.01686 0.01033 -0.0819 0.6671 0.8949
0.750 0.5166 0.01692 0.01042 -0.0805 0.6621 0.8997
1.000 0.5411 0.01693 0.01038 -0.0804 0.6577 0.9041
1.250 0.5689 0.01687 0.01025 -0.0806 0.6542 0.9070
1.500 0.5997 0.01689 0.01016 -0.0814 0.6513 0.9098
1.750 0.6170 0.01699 0.01033 -0.0799 0.6460 0.9138
2.000 0.6416 0.01703 0.01035 -0.0798 0.6415 0.9177
2.250 0.6705 0.01701 0.01028 -0.0803 0.6380 0.9204
2.500 0.7020 0.01703 0.01020 -0.0813 0.6351 0.9227
2.750 0.7185 0.01716 0.01044 -0.0796 0.6296 0.9272
3.000 0.7433 0.01722 0.01049 -0.0795 0.6251 0.9309
3.250 0.7733 0.01723 0.01047 -0.0803 0.6215 0.9338
3.500 0.8051 0.01724 0.01040 -0.0813 0.6183 0.9361
3.750 0.8207 0.01740 0.01069 -0.0794 0.6124 0.9410
4.000 0.8468 0.01743 0.01071 -0.0795 0.6078 0.9452
4.250 0.8785 0.01738 0.01063 -0.0805 0.6042 0.9482
4.500 0.9040 0.01750 0.01079 -0.0805 0.5995 0.9520
4.750 0.9261 0.01761 0.01097 -0.0799 0.5938 0.9568
5.000 0.9567 0.01756 0.01092 -0.0807 0.5895 0.9609
5.250 0.9937 0.01755 0.01084 -0.0827 0.5858 0.9640
5.500 1.0133 0.01776 0.01121 -0.0819 0.5790 0.9706
5.750 1.0475 0.01773 0.01120 -0.0835 0.5740 0.9744
6.000 1.0874 0.01768 0.01109 -0.0861 0.5699 0.9772
6.250 1.1118 0.01792 0.01150 -0.0864 0.5625 0.9842
6.500 1.1504 0.01786 0.01145 -0.0889 0.5572 0.9882
6.750 1.1844 0.01795 0.01159 -0.0907 0.5512 0.9967
7.000 1.2016 0.01806 0.01179 -0.0893 0.5446 1.0000
7.250 1.2348 0.01795 0.01163 -0.0906 0.5395 1.0000
7.500 1.2515 0.01820 0.01203 -0.0894 0.5317 1.0000
7.750 1.2823 0.01815 0.01198 -0.0904 0.5253 1.0000
8.000 1.3048 0.01834 0.01227 -0.0901 0.5175 1.0000
8.250 1.3335 0.01832 0.01226 -0.0907 0.5099 1.0000
8.500 1.3550 0.01852 0.01257 -0.0902 0.5013 1.0000
8.750 1.3835 0.01851 0.01255 -0.0907 0.4931 1.0000
9.000 1.4002 0.01878 0.01294 -0.0894 0.4830 1.0000
9.250 1.4229 0.01891 0.01311 -0.0890 0.4736 1.0000
9.500 1.4401 0.01910 0.01334 -0.0876 0.4630 1.0000
9.750 1.4506 0.01946 0.01378 -0.0851 0.4518 1.0000
10.000 1.4636 0.01981 0.01416 -0.0831 0.4403 1.0000
10.250 1.4756 0.02023 0.01459 -0.0810 0.4282 1.0000
10.500 1.4848 0.02077 0.01512 -0.0786 0.4151 1.0000
10.750 1.4893 0.02151 0.01591 -0.0757 0.4010 1.0000
11.000 1.4929 0.02239 0.01681 -0.0728 0.3862 1.0000
11.250 1.4952 0.02345 0.01787 -0.0701 0.3711 1.0000
11.500 1.4960 0.02470 0.01911 -0.0673 0.3554 1.0000
11.750 1.4954 0.02616 0.02055 -0.0647 0.3395 1.0000
12.000 1.4936 0.02783 0.02219 -0.0623 0.3235 1.0000
12.250 1.4907 0.02971 0.02405 -0.0600 0.3074 1.0000
12.500 1.4873 0.03176 0.02609 -0.0579 0.2915 1.0000
12.750 1.4836 0.03397 0.02827 -0.0561 0.2764 1.0000
13.000 1.4795 0.03633 0.03061 -0.0544 0.2615 1.0000
13.250 1.4752 0.03883 0.03308 -0.0529 0.2472 1.0000
13.500 1.4708 0.04146 0.03569 -0.0516 0.2334 1.0000
13.750 1.4669 0.04418 0.03843 -0.0506 0.2198 1.0000
14.000 1.4631 0.04700 0.04125 -0.0497 0.2067 1.0000
14.250 1.4594 0.04992 0.04418 -0.0490 0.1941 1.0000
14.500 1.4555 0.05297 0.04724 -0.0485 0.1819 1.0000
14.750 1.4513 0.05612 0.05039 -0.0480 0.1705 1.0000
15.000 1.4460 0.05948 0.05371 -0.0477 0.1598 1.0000
15.250 1.4423 0.06283 0.05709 -0.0476 0.1489 1.0000
15.500 1.4392 0.06619 0.06049 -0.0477 0.1386 1.0000
15.750 1.4349 0.06974 0.06405 -0.0478 0.1292 1.0000
16.000 1.4290 0.07355 0.06783 -0.0480 0.1206 1.0000
16.250 1.4266 0.07711 0.07148 -0.0485 0.1116 1.0000
16.500 1.4224 0.08091 0.07530 -0.0489 0.1037 1.0000
16.750 1.4171 0.08490 0.07927 -0.0496 0.0966 1.0000
17.000 1.4146 0.08864 0.08311 -0.0503 0.0893 1.0000
17.250 1.4091 0.09274 0.08714 -0.0511 0.0833 1.0000
17.500 1.4069 0.09663 0.09117 -0.0521 0.0772 1.0000
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