EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 432 AIRFOIL (e432-il) Reynolds number: 500,000 Max Cl/Cd: 108.34 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e432-il-500000-n5.txt Download as CSV file: xf-e432-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1199 0.08623 0.08322 -0.1110 0.8510 0.0066
-11.250 -0.1236 0.08167 0.07853 -0.1130 0.8247 0.0065
-10.750 -0.2212 0.05210 0.04886 -0.1287 0.7944 0.0062
-10.500 -0.2829 0.04105 0.03741 -0.1335 0.7780 0.0061
-10.250 -0.3176 0.03624 0.03227 -0.1320 0.7638 0.0061
-10.000 -0.3380 0.03324 0.02899 -0.1291 0.7516 0.0060
-9.750 -0.3589 0.03046 0.02588 -0.1247 0.7412 0.0060
-9.500 -0.3634 0.02798 0.02303 -0.1219 0.7326 0.0061
-9.250 -0.3590 0.02595 0.02068 -0.1198 0.7247 0.0062
-9.000 -0.3481 0.02446 0.01888 -0.1181 0.7178 0.0064
-8.750 -0.3348 0.02297 0.01712 -0.1167 0.7114 0.0065
-8.500 -0.3187 0.02175 0.01565 -0.1154 0.7048 0.0065
-8.250 -0.3004 0.02071 0.01437 -0.1144 0.6992 0.0066
-8.000 -0.2807 0.01974 0.01324 -0.1135 0.6934 0.0066
-7.750 -0.2610 0.01867 0.01199 -0.1126 0.6882 0.0067
-7.500 -0.2402 0.01778 0.01095 -0.1118 0.6835 0.0067
-7.250 -0.2186 0.01693 0.00999 -0.1112 0.6787 0.0068
-7.000 -0.1961 0.01627 0.00923 -0.1105 0.6736 0.0069
-6.750 -0.1732 0.01570 0.00856 -0.1100 0.6691 0.0070
-6.500 -0.1497 0.01515 0.00795 -0.1095 0.6652 0.0072
-6.250 -0.1255 0.01467 0.00739 -0.1091 0.6610 0.0073
-6.000 -0.1013 0.01422 0.00688 -0.1086 0.6567 0.0075
-5.750 -0.0769 0.01382 0.00640 -0.1082 0.6526 0.0078
-5.500 -0.0519 0.01343 0.00595 -0.1079 0.6490 0.0080
-5.250 -0.0264 0.01307 0.00553 -0.1077 0.6453 0.0085
-5.000 -0.0007 0.01275 0.00515 -0.1075 0.6416 0.0090
-4.750 0.0249 0.01243 0.00479 -0.1072 0.6378 0.0097
-4.500 0.0510 0.01219 0.00448 -0.1071 0.6344 0.0107
-4.250 0.0776 0.01193 0.00420 -0.1070 0.6311 0.0121
-4.000 0.1043 0.01168 0.00394 -0.1070 0.6276 0.0153
-3.750 0.1310 0.01146 0.00372 -0.1070 0.6240 0.0208
-3.500 0.1576 0.01125 0.00353 -0.1069 0.6206 0.0327
-3.250 0.1845 0.01103 0.00337 -0.1070 0.6175 0.0498
-3.000 0.2117 0.01078 0.00322 -0.1072 0.6144 0.0754
-2.750 0.2388 0.01050 0.00309 -0.1074 0.6110 0.1152
-2.500 0.2656 0.01015 0.00295 -0.1076 0.6075 0.1808
-2.250 0.2925 0.00974 0.00281 -0.1080 0.6043 0.2726
-2.000 0.3199 0.00925 0.00266 -0.1085 0.6015 0.3886
-1.750 0.3477 0.00853 0.00255 -0.1093 0.5983 0.5676
-1.500 0.3751 0.00840 0.00268 -0.1093 0.5948 0.6627
-1.250 0.4032 0.00845 0.00273 -0.1093 0.5914 0.6894
-1.000 0.4314 0.00852 0.00276 -0.1094 0.5884 0.7045
-0.750 0.4596 0.00861 0.00280 -0.1095 0.5854 0.7168
-0.500 0.4879 0.00868 0.00287 -0.1096 0.5820 0.7306
-0.250 0.5154 0.00880 0.00300 -0.1094 0.5786 0.7474
0.000 0.5429 0.00893 0.00310 -0.1093 0.5752 0.7583
0.250 0.5711 0.00900 0.00311 -0.1095 0.5720 0.7622
0.500 0.5992 0.00905 0.00313 -0.1096 0.5688 0.7642
0.750 0.6274 0.00908 0.00316 -0.1098 0.5654 0.7663
1.000 0.6556 0.00913 0.00319 -0.1100 0.5618 0.7684
1.250 0.6836 0.00919 0.00322 -0.1102 0.5582 0.7704
1.500 0.7114 0.00927 0.00325 -0.1104 0.5549 0.7728
1.750 0.7398 0.00933 0.00329 -0.1106 0.5514 0.7751
2.000 0.7681 0.00938 0.00334 -0.1109 0.5475 0.7771
2.250 0.7956 0.00944 0.00339 -0.1110 0.5435 0.7788
2.500 0.8227 0.00952 0.00345 -0.1110 0.5398 0.7804
2.750 0.8501 0.00959 0.00353 -0.1111 0.5357 0.7823
3.000 0.8774 0.00966 0.00361 -0.1112 0.5312 0.7844
3.250 0.9043 0.00975 0.00368 -0.1112 0.5265 0.7866
3.500 0.9310 0.00985 0.00377 -0.1112 0.5220 0.7887
3.750 0.9583 0.00992 0.00387 -0.1113 0.5169 0.7909
4.000 0.9849 0.01002 0.00396 -0.1113 0.5115 0.7930
4.250 1.0109 0.01014 0.00406 -0.1111 0.5065 0.7949
4.500 1.0372 0.01022 0.00419 -0.1110 0.5009 0.7968
4.750 1.0624 0.01034 0.00431 -0.1108 0.4949 0.7989
5.000 1.0878 0.01046 0.00445 -0.1105 0.4893 0.8013
5.250 1.1133 0.01058 0.00460 -0.1103 0.4829 0.8036
5.500 1.1374 0.01075 0.00475 -0.1098 0.4765 0.8060
5.750 1.1629 0.01087 0.00491 -0.1096 0.4695 0.8084
6.250 1.2102 0.01120 0.00527 -0.1086 0.4544 0.8127
6.500 1.2318 0.01141 0.00547 -0.1077 0.4462 0.8151
6.750 1.2546 0.01158 0.00569 -0.1070 0.4374 0.8179
7.000 1.2751 0.01182 0.00593 -0.1059 0.4281 0.8209
7.250 1.2948 0.01205 0.00617 -0.1047 0.4178 0.8240
7.750 1.3285 0.01261 0.00673 -0.1011 0.3952 0.8298
8.000 1.3431 0.01298 0.00709 -0.0990 0.3823 0.8330
8.250 1.3569 0.01340 0.00750 -0.0968 0.3688 0.8366
8.500 1.3700 0.01387 0.00795 -0.0946 0.3543 0.8405
8.750 1.3809 0.01442 0.00848 -0.0921 0.3384 0.8445
9.000 1.3901 0.01503 0.00908 -0.0894 0.3220 0.8490
9.250 1.3986 0.01573 0.00975 -0.0867 0.3062 0.8541
9.750 1.4108 0.01743 0.01141 -0.0810 0.2741 0.8646
10.000 1.4152 0.01845 0.01241 -0.0782 0.2585 0.8712
10.250 1.4191 0.01955 0.01350 -0.0755 0.2442 0.8781
10.500 1.4220 0.02076 0.01471 -0.0728 0.2301 0.8872
10.750 1.4242 0.02205 0.01602 -0.0702 0.2173 0.8985
11.000 1.4255 0.02342 0.01741 -0.0676 0.2044 0.9153
11.250 1.4288 0.02487 0.01891 -0.0658 0.1910 0.9705
11.750 1.4369 0.02821 0.02223 -0.0628 0.1685 1.0000
12.000 1.4397 0.03010 0.02410 -0.0614 0.1576 1.0000
12.250 1.4414 0.03214 0.02612 -0.0601 0.1463 1.0000
12.500 1.4438 0.03418 0.02816 -0.0590 0.1355 1.0000
12.750 1.4461 0.03630 0.03026 -0.0580 0.1253 1.0000
13.000 1.4484 0.03846 0.03243 -0.0570 0.1167 1.0000
13.500 1.4536 0.04292 0.03690 -0.0555 0.1007 1.0000
13.750 1.4549 0.04537 0.03936 -0.0549 0.0932 1.0000
14.000 1.4568 0.04782 0.04182 -0.0543 0.0859 1.0000
14.250 1.4595 0.05023 0.04426 -0.0539 0.0797 1.0000
14.500 1.4598 0.05296 0.04699 -0.0535 0.0730 1.0000
14.750 1.4622 0.05554 0.04960 -0.0533 0.0670 1.0000
15.000 1.4630 0.05833 0.05242 -0.0531 0.0616 1.0000
15.250 1.4646 0.06111 0.05522 -0.0531 0.0561 1.0000
15.500 1.4654 0.06403 0.05818 -0.0531 0.0516 1.0000
15.750 1.4664 0.06699 0.06118 -0.0532 0.0470 1.0000
16.000 1.4671 0.07004 0.06427 -0.0534 0.0431 1.0000
16.250 1.4658 0.07340 0.06764 -0.0537 0.0387 1.0000
16.500 1.4683 0.07633 0.07065 -0.0541 0.0365 1.0000
16.750 1.4668 0.07985 0.07420 -0.0546 0.0326 1.0000
17.000 1.4670 0.08320 0.07761 -0.0552 0.0299 1.0000
17.250 1.4668 0.08662 0.08109 -0.0559 0.0275 1.0000
17.500 1.4654 0.09028 0.08481 -0.0567 0.0249 1.0000
17.750 1.4649 0.09387 0.08846 -0.0576 0.0230 1.0000
18.000 1.4629 0.09772 0.09237 -0.0586 0.0207 1.0000
18.250 1.4615 0.10152 0.09624 -0.0597 0.0190 1.0000
18.500 1.4594 0.10546 0.10024 -0.0609 0.0174 1.0000
18.750 1.4579 0.10933 0.10419 -0.0622 0.0159 1.0000
19.000 1.4549 0.11349 0.10842 -0.0637 0.0147 1.0000
19.250 1.4533 0.11745 0.11246 -0.0651 0.0133 1.0000
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Polar data table (+)
Polar graphs
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