EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 100,000 Max Cl/Cd: 49.8 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e433-il-100000-n5.txt Download as CSV file: xf-e433-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 433 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2359 0.09811 0.09318 -0.0866 0.9594 0.0292
-9.500 -0.2255 0.09615 0.09120 -0.0858 0.9546 0.0276
-9.000 -0.2252 0.08242 0.07749 -0.0975 0.9459 0.0231
-8.750 -0.2274 0.07888 0.07398 -0.0990 0.9386 0.0227
-8.500 -0.2265 0.07343 0.06852 -0.1044 0.9336 0.0223
-8.250 -0.2364 0.06921 0.06426 -0.1068 0.9257 0.0220
-8.000 -0.2463 0.06498 0.05994 -0.1091 0.9186 0.0216
-7.750 -0.2590 0.06146 0.05631 -0.1085 0.9097 0.0213
-7.500 -0.2621 0.05690 0.05152 -0.1096 0.9039 0.0207
-7.250 -0.2690 0.05337 0.04776 -0.1080 0.8965 0.0203
-7.000 -0.2701 0.04921 0.04324 -0.1070 0.8902 0.0198
-6.750 -0.2588 0.04405 0.03747 -0.1076 0.8870 0.0192
-6.500 -0.2636 0.04135 0.03432 -0.1035 0.8783 0.0189
-6.250 -0.2454 0.03842 0.03091 -0.1033 0.8748 0.0188
-6.000 -0.2201 0.03571 0.02778 -0.1040 0.8726 0.0190
-5.750 -0.2061 0.03408 0.02588 -0.1022 0.8673 0.0193
-5.500 -0.1891 0.03258 0.02409 -0.1008 0.8623 0.0196
-5.250 -0.1617 0.03084 0.02206 -0.1011 0.8597 0.0202
-5.000 -0.1307 0.02939 0.02031 -0.1019 0.8578 0.0219
-4.750 -0.0980 0.02801 0.01873 -0.1029 0.8564 0.0244
-4.500 -0.0931 0.02771 0.01837 -0.0991 0.8483 0.0255
-4.250 -0.0661 0.02664 0.01716 -0.0990 0.8453 0.0276
-4.000 -0.0361 0.02555 0.01600 -0.0995 0.8432 0.0303
-3.750 -0.0036 0.02467 0.01505 -0.1006 0.8416 0.0368
-3.250 0.0299 0.02379 0.01420 -0.0973 0.8305 0.0582
-3.000 0.0602 0.02289 0.01354 -0.0981 0.8283 0.1045
-2.500 0.0941 0.02071 0.01346 -0.0957 0.8194 0.5403
-2.250 0.1063 0.02108 0.01417 -0.0911 0.8148 0.6992
-2.000 0.1330 0.02136 0.01429 -0.0899 0.8123 0.7526
-1.750 0.1600 0.02156 0.01434 -0.0886 0.8105 0.7836
-1.500 0.1580 0.02218 0.01493 -0.0829 0.8007 0.8003
-1.250 0.1743 0.02236 0.01502 -0.0790 0.7976 0.8266
-1.000 0.1902 0.02237 0.01498 -0.0748 0.7953 0.8541
-0.750 0.1829 0.02291 0.01551 -0.0681 0.7850 0.8732
-0.500 0.2090 0.02272 0.01517 -0.0672 0.7824 0.8831
-0.250 0.2443 0.02248 0.01477 -0.0687 0.7806 0.8874
0.000 0.2501 0.02294 0.01518 -0.0655 0.7710 0.8935
0.250 0.2815 0.02275 0.01486 -0.0662 0.7681 0.8972
0.500 0.3171 0.02249 0.01448 -0.0677 0.7661 0.9005
1.000 0.3581 0.02276 0.01462 -0.0660 0.7536 0.9096
1.250 0.3939 0.02247 0.01424 -0.0675 0.7513 0.9126
1.750 0.4378 0.02270 0.01439 -0.0662 0.7387 0.9219
2.000 0.4741 0.02236 0.01401 -0.0677 0.7363 0.9251
2.500 0.5203 0.02254 0.01417 -0.0669 0.7234 0.9350
2.750 0.5585 0.02214 0.01375 -0.0686 0.7210 0.9384
3.000 0.5714 0.02260 0.01423 -0.0668 0.7110 0.9465
3.250 0.6089 0.02223 0.01386 -0.0684 0.7076 0.9502
3.500 0.6460 0.02190 0.01355 -0.0701 0.7038 0.9542
3.750 0.6666 0.02220 0.01391 -0.0696 0.6942 0.9627
4.000 0.7095 0.02169 0.01341 -0.0721 0.6910 0.9673
4.250 0.7315 0.02203 0.01383 -0.0721 0.6805 0.9828
4.500 0.7725 0.02146 0.01329 -0.0742 0.6763 1.0000
4.750 0.7892 0.02184 0.01372 -0.0731 0.6655 1.0000
5.000 0.8305 0.02130 0.01323 -0.0753 0.6607 1.0000
5.250 0.8481 0.02166 0.01365 -0.0743 0.6491 1.0000
5.500 0.8752 0.02167 0.01371 -0.0745 0.6394 1.0000
5.750 0.9111 0.02133 0.01342 -0.0758 0.6311 1.0000
6.000 0.9324 0.02158 0.01374 -0.0752 0.6185 1.0000
6.250 0.9575 0.02169 0.01390 -0.0751 0.6060 1.0000
6.500 0.9847 0.02171 0.01397 -0.0753 0.5930 1.0000
6.750 1.0119 0.02174 0.01407 -0.0754 0.5789 1.0000
7.000 1.0379 0.02183 0.01419 -0.0753 0.5635 1.0000
7.250 1.0628 0.02197 0.01437 -0.0751 0.5466 1.0000
7.500 1.0875 0.02213 0.01455 -0.0748 0.5282 1.0000
7.750 1.1120 0.02233 0.01473 -0.0744 0.5088 1.0000
8.000 1.1306 0.02279 0.01520 -0.0734 0.4877 1.0000
8.250 1.1504 0.02324 0.01563 -0.0724 0.4660 1.0000
8.500 1.1672 0.02384 0.01620 -0.0712 0.4440 1.0000
8.750 1.1822 0.02454 0.01686 -0.0697 0.4216 1.0000
9.000 1.1960 0.02533 0.01762 -0.0682 0.3997 1.0000
9.250 1.2079 0.02624 0.01851 -0.0665 0.3776 1.0000
9.500 1.2189 0.02721 0.01944 -0.0647 0.3564 1.0000
9.750 1.2285 0.02830 0.02052 -0.0629 0.3348 1.0000
10.000 1.2373 0.02947 0.02165 -0.0611 0.3141 1.0000
10.250 1.2454 0.03072 0.02288 -0.0593 0.2941 1.0000
10.500 1.2527 0.03206 0.02423 -0.0575 0.2739 1.0000
10.750 1.2592 0.03350 0.02565 -0.0558 0.2551 1.0000
11.250 1.2708 0.03663 0.02877 -0.0526 0.2192 1.0000
11.500 1.2761 0.03831 0.03047 -0.0511 0.2022 1.0000
11.750 1.2807 0.04011 0.03228 -0.0496 0.1860 1.0000
12.000 1.2846 0.04202 0.03423 -0.0483 0.1706 1.0000
12.250 1.2881 0.04403 0.03626 -0.0470 0.1563 1.0000
12.500 1.2912 0.04616 0.03841 -0.0459 0.1427 1.0000
12.750 1.2938 0.04840 0.04069 -0.0448 0.1302 1.0000
13.000 1.2955 0.05080 0.04313 -0.0439 0.1187 1.0000
13.250 1.2960 0.05339 0.04574 -0.0430 0.1086 1.0000
13.500 1.2969 0.05605 0.04846 -0.0423 0.0987 1.0000
13.750 1.2983 0.05875 0.05126 -0.0418 0.0897 1.0000
14.000 1.2971 0.06179 0.05436 -0.0414 0.0825 1.0000
14.250 1.2967 0.06484 0.05752 -0.0411 0.0754 1.0000
14.500 1.2954 0.06810 0.06087 -0.0409 0.0697 1.0000
14.750 1.2937 0.07150 0.06438 -0.0410 0.0642 1.0000
15.000 1.2906 0.07515 0.06810 -0.0412 0.0598 1.0000
15.250 1.2893 0.07869 0.07180 -0.0415 0.0553 1.0000
15.500 1.2843 0.08278 0.07595 -0.0421 0.0521 1.0000
15.750 1.2825 0.08655 0.07988 -0.0427 0.0484 1.0000
16.000 1.2795 0.09057 0.08404 -0.0436 0.0453 1.0000
16.250 1.2743 0.09495 0.08849 -0.0447 0.0429 1.0000
16.500 1.2717 0.09906 0.09276 -0.0458 0.0403 1.0000
16.750 1.2686 0.10335 0.09722 -0.0471 0.0378 1.0000
17.000 1.2640 0.10792 0.10192 -0.0488 0.0358 1.0000
17.250 1.2597 0.11235 0.10637 -0.0505 0.0341 1.0000
17.500 1.2564 0.11695 0.11124 -0.0523 0.0322 1.0000
17.750 1.2521 0.12171 0.11618 -0.0544 0.0305 1.0000
18.000 1.2475 0.12658 0.12116 -0.0568 0.0290 1.0000
18.250 1.2436 0.13126 0.12589 -0.0592 0.0278 1.0000
18.500 1.2391 0.13624 0.13104 -0.0618 0.0266 1.0000
18.750 1.2322 0.14194 0.13698 -0.0650 0.0254 1.0000
19.000 1.2252 0.14772 0.14293 -0.0684 0.0244 1.0000
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Polar data table (+)
Polar graphs
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