EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 432 AIRFOIL (e432-il) Reynolds number: 100,000 Max Cl/Cd: 45.48 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e432-il-100000-n5.txt Download as CSV file: xf-e432-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2467 0.13631 0.13139 -0.0521 1.0000 0.0473
-12.000 -0.2472 0.13370 0.12885 -0.0521 1.0000 0.0480
-11.750 -0.2498 0.13127 0.12650 -0.0519 1.0000 0.0488
-11.500 -0.2427 0.12722 0.12250 -0.0554 0.9961 0.0498
-11.250 -0.2369 0.12216 0.11746 -0.0620 0.9876 0.0511
-11.000 -0.2292 0.11713 0.11244 -0.0674 0.9775 0.0513
-10.750 -0.2158 0.10900 0.10425 -0.0695 0.9692 0.0302
-10.250 -0.2008 0.09747 0.09273 -0.0783 0.9470 0.0254
-10.000 -0.1868 0.09331 0.08856 -0.0822 0.9367 0.0249
-9.750 -0.1747 0.08799 0.08323 -0.0875 0.9277 0.0242
-9.500 -0.1661 0.08192 0.07714 -0.0937 0.9169 0.0235
-9.250 -0.1862 0.06642 0.06153 -0.1086 0.9026 0.0213
-9.000 -0.1857 0.06090 0.05587 -0.1146 0.8881 0.0211
-8.750 -0.1942 0.05591 0.05067 -0.1184 0.8717 0.0209
-8.500 -0.2041 0.05244 0.04698 -0.1189 0.8562 0.0208
-8.250 -0.2112 0.04879 0.04303 -0.1188 0.8435 0.0207
-8.000 -0.2113 0.04546 0.03935 -0.1185 0.8333 0.0204
-7.750 -0.2116 0.04237 0.03592 -0.1171 0.8223 0.0203
-7.500 -0.2055 0.03920 0.03229 -0.1161 0.8140 0.0203
-7.250 -0.1974 0.03635 0.02898 -0.1146 0.8051 0.0204
-7.000 -0.1820 0.03370 0.02584 -0.1138 0.7985 0.0206
-6.750 -0.1666 0.03148 0.02315 -0.1124 0.7905 0.0211
-6.500 -0.1446 0.02996 0.02136 -0.1121 0.7846 0.0222
-6.250 -0.1238 0.02888 0.02010 -0.1115 0.7778 0.0236
-6.000 -0.1008 0.02738 0.01823 -0.1108 0.7715 0.0250
-5.750 -0.0747 0.02596 0.01655 -0.1105 0.7668 0.0262
-5.500 -0.0534 0.02500 0.01552 -0.1096 0.7601 0.0274
-5.250 -0.0292 0.02398 0.01435 -0.1090 0.7547 0.0292
-5.000 -0.0037 0.02309 0.01335 -0.1087 0.7503 0.0321
-4.750 0.0171 0.02251 0.01268 -0.1076 0.7440 0.0364
-4.500 0.0394 0.02180 0.01197 -0.1069 0.7387 0.0409
-4.250 0.0640 0.02114 0.01125 -0.1065 0.7346 0.0494
-4.000 0.0850 0.02058 0.01071 -0.1055 0.7293 0.0625
-3.750 0.1067 0.02004 0.01024 -0.1046 0.7239 0.0854
-3.500 0.1299 0.01936 0.00978 -0.1041 0.7197 0.1321
-3.250 0.1511 0.01856 0.00943 -0.1036 0.7156 0.2321
-3.000 0.1650 0.01748 0.00929 -0.1020 0.7102 0.4341
-2.750 0.1765 0.01757 0.01022 -0.0970 0.7058 0.6486
-2.500 0.2009 0.01795 0.01043 -0.0956 0.7020 0.7124
-2.250 0.2220 0.01837 0.01073 -0.0936 0.6976 0.7451
-2.000 0.2405 0.01880 0.01107 -0.0910 0.6926 0.7665
-1.750 0.2612 0.01913 0.01128 -0.0887 0.6885 0.7860
-1.500 0.2823 0.01945 0.01146 -0.0862 0.6851 0.8079
-1.250 0.2970 0.01980 0.01176 -0.0827 0.6806 0.8283
-1.000 0.3131 0.02004 0.01193 -0.0797 0.6759 0.8443
-0.750 0.3363 0.02009 0.01187 -0.0785 0.6720 0.8528
-0.500 0.3634 0.02005 0.01166 -0.0785 0.6687 0.8595
-0.250 0.3846 0.02012 0.01166 -0.0774 0.6642 0.8641
0.000 0.4057 0.02020 0.01167 -0.0765 0.6593 0.8693
0.250 0.4310 0.02021 0.01158 -0.0765 0.6555 0.8744
0.500 0.4599 0.02017 0.01140 -0.0767 0.6523 0.8774
0.750 0.4808 0.02029 0.01149 -0.0758 0.6478 0.8815
1.000 0.5017 0.02042 0.01159 -0.0750 0.6430 0.8861
1.250 0.5278 0.02047 0.01156 -0.0751 0.6391 0.8899
1.500 0.5572 0.02045 0.01145 -0.0755 0.6361 0.8928
1.750 0.5775 0.02062 0.01162 -0.0746 0.6314 0.8969
2.000 0.5979 0.02081 0.01181 -0.0738 0.6265 0.9011
2.250 0.6244 0.02089 0.01184 -0.0739 0.6226 0.9049
2.500 0.6543 0.02088 0.01176 -0.0745 0.6196 0.9080
2.750 0.6724 0.02114 0.01207 -0.0732 0.6146 0.9127
3.000 0.6930 0.02137 0.01232 -0.0725 0.6096 0.9173
3.250 0.7205 0.02144 0.01236 -0.0728 0.6059 0.9208
3.500 0.7521 0.02142 0.01230 -0.0736 0.6029 0.9243
3.750 0.7651 0.02184 0.01283 -0.0717 0.5969 0.9308
4.000 0.7881 0.02203 0.01305 -0.0713 0.5921 0.9358
4.250 0.8186 0.02206 0.01306 -0.0721 0.5886 0.9397
4.500 0.8456 0.02220 0.01323 -0.0723 0.5845 0.9448
4.750 0.8615 0.02266 0.01380 -0.0711 0.5780 0.9522
5.000 0.8919 0.02272 0.01389 -0.0719 0.5737 0.9582
5.250 0.9296 0.02263 0.01380 -0.0739 0.5705 0.9627
5.500 0.9451 0.02331 0.01463 -0.0730 0.5629 0.9744
5.750 0.9781 0.02339 0.01475 -0.0745 0.5580 0.9852
6.000 1.0159 0.02322 0.01459 -0.0765 0.5544 1.0000
6.250 1.0194 0.02406 0.01558 -0.0737 0.5462 1.0000
6.500 1.0494 0.02409 0.01563 -0.0744 0.5413 1.0000
7.000 1.0874 0.02490 0.01660 -0.0731 0.5284 1.0000
7.250 1.1238 0.02471 0.01643 -0.0746 0.5238 1.0000
7.500 1.1262 0.02560 0.01745 -0.0716 0.5154 1.0000
7.750 1.1563 0.02556 0.01745 -0.0722 0.5096 1.0000
8.000 1.1653 0.02630 0.01830 -0.0702 0.5017 1.0000
8.250 1.1891 0.02645 0.01850 -0.0699 0.4947 1.0000
8.500 1.1998 0.02717 0.01933 -0.0682 0.4866 1.0000
8.750 1.2217 0.02736 0.01958 -0.0677 0.4789 1.0000
9.000 1.2274 0.02834 0.02067 -0.0655 0.4698 1.0000
9.250 1.2541 0.02829 0.02065 -0.0655 0.4620 1.0000
9.500 1.2525 0.02971 0.02220 -0.0628 0.4514 1.0000
9.750 1.2687 0.03023 0.02278 -0.0618 0.4422 1.0000
10.000 1.2816 0.03093 0.02354 -0.0605 0.4319 1.0000
10.250 1.2826 0.03247 0.02518 -0.0585 0.4206 1.0000
10.500 1.2921 0.03350 0.02629 -0.0572 0.4092 1.0000
10.750 1.3059 0.03424 0.02707 -0.0562 0.3978 1.0000
11.000 1.3136 0.03546 0.02834 -0.0549 0.3852 1.0000
11.250 1.3155 0.03722 0.03017 -0.0534 0.3720 1.0000
11.500 1.3197 0.03887 0.03187 -0.0522 0.3586 1.0000
11.750 1.3243 0.04053 0.03358 -0.0510 0.3450 1.0000
12.000 1.3287 0.04225 0.03532 -0.0499 0.3309 1.0000
12.250 1.3326 0.04407 0.03716 -0.0489 0.3169 1.0000
12.500 1.3359 0.04600 0.03910 -0.0480 0.3028 1.0000
12.750 1.3389 0.04801 0.04111 -0.0471 0.2890 1.0000
13.000 1.3409 0.05017 0.04327 -0.0463 0.2752 1.0000
13.250 1.3426 0.05244 0.04555 -0.0456 0.2618 1.0000
13.500 1.3427 0.05495 0.04807 -0.0450 0.2484 1.0000
13.750 1.3420 0.05768 0.05085 -0.0445 0.2356 1.0000
14.000 1.3412 0.06049 0.05369 -0.0442 0.2230 1.0000
14.250 1.3406 0.06336 0.05659 -0.0440 0.2111 1.0000
14.500 1.3398 0.06630 0.05955 -0.0439 0.1997 1.0000
14.750 1.3385 0.06935 0.06260 -0.0439 0.1887 1.0000
15.000 1.3367 0.07264 0.06598 -0.0441 0.1778 1.0000
15.250 1.3347 0.07602 0.06942 -0.0443 0.1673 1.0000
15.500 1.3326 0.07943 0.07285 -0.0447 0.1577 1.0000
15.750 1.3300 0.08300 0.07647 -0.0452 0.1484 1.0000
16.000 1.3276 0.08666 0.08021 -0.0459 0.1393 1.0000
16.250 1.3249 0.09037 0.08395 -0.0466 0.1311 1.0000
16.500 1.3216 0.09428 0.08794 -0.0475 0.1229 1.0000
16.750 1.3190 0.09814 0.09188 -0.0485 0.1154 1.0000
17.000 1.3150 0.10222 0.09598 -0.0496 0.1085 1.0000
17.250 1.3125 0.10621 0.10010 -0.0509 0.1016 1.0000
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Polar data table (+)
Polar graphs
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