EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 100,000 Max Cl/Cd: 52.87 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e433-il-100000.txt Download as CSV file: xf-e433-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4311 0.11129 0.10730 -0.0339 0.9938 0.0916
-7.750 -0.4565 0.10792 0.10400 -0.0403 0.9879 0.0931
-7.500 -0.4839 0.10419 0.10025 -0.0467 0.9824 0.0935
-7.250 -0.4354 0.09988 0.09598 -0.0408 0.9812 0.0980
-7.000 -0.4394 0.09710 0.09323 -0.0413 0.9766 0.1005
-6.750 -0.4460 0.09287 0.08899 -0.0467 0.9720 0.1038
-6.500 -0.4726 0.08898 0.08500 -0.0504 0.9658 0.1071
-6.250 -0.4785 0.08381 0.07967 -0.0543 0.9612 0.1099
-6.000 -0.4571 0.08094 0.07692 -0.0529 0.9577 0.1138
-5.750 -0.4591 0.07793 0.07382 -0.0531 0.9530 0.1198
-5.500 -0.4541 0.07348 0.06919 -0.0561 0.9487 0.1267
-5.250 -0.4405 0.07016 0.06550 -0.0598 0.9440 0.1401
-5.000 -0.4313 0.06713 0.06264 -0.0576 0.9400 0.1436
-4.750 -0.4160 0.06397 0.05928 -0.0594 0.9356 0.1577
-4.500 -0.3885 0.06084 0.05604 -0.0621 0.9317 0.1743
-4.250 -0.3785 0.05844 0.05357 -0.0613 0.9267 0.1903
-4.000 -0.3106 0.04543 0.03828 -0.0670 0.9241 0.0612
-3.750 -0.2723 0.04198 0.03395 -0.0681 0.9202 0.0529
-3.500 -0.2288 0.03980 0.03128 -0.0709 0.9167 0.0523
-3.250 -0.2114 0.03878 0.02991 -0.0692 0.9108 0.0540
-3.000 -0.1807 0.03701 0.02795 -0.0698 0.9063 0.0565
-2.750 -0.1410 0.03583 0.02668 -0.0716 0.9025 0.0600
-2.500 -0.1207 0.03527 0.02597 -0.0703 0.8966 0.0662
-2.250 -0.0934 0.03435 0.02518 -0.0705 0.8915 0.0782
-2.000 -0.0541 0.03314 0.02428 -0.0726 0.8877 0.1247
-1.750 -0.0502 0.03067 0.02490 -0.0675 0.8829 0.7246
-1.500 -0.0535 0.03155 0.02578 -0.0593 0.8761 0.8118
-1.250 -0.0478 0.03222 0.02635 -0.0519 0.8713 0.8630
-1.000 -0.0574 0.03228 0.02637 -0.0445 0.8630 0.8903
-0.750 -0.0497 0.03232 0.02631 -0.0385 0.8575 0.9309
-0.500 0.1619 0.03434 0.02762 -0.0710 0.8579 1.0000
-0.250 0.1612 0.03450 0.02770 -0.0673 0.8491 1.0000
0.000 0.1859 0.03460 0.02764 -0.0676 0.8430 1.0000
0.250 0.1855 0.03476 0.02773 -0.0638 0.8338 1.0000
0.500 0.2116 0.03483 0.02768 -0.0642 0.8276 1.0000
0.750 0.2088 0.03498 0.02777 -0.0601 0.8178 1.0000
1.000 0.2371 0.03506 0.02773 -0.0607 0.8121 1.0000
1.250 0.2345 0.03521 0.02784 -0.0566 0.8016 1.0000
1.500 0.2699 0.03531 0.02782 -0.0583 0.7965 1.0000
1.750 0.2773 0.03567 0.02813 -0.0561 0.7859 1.0000
2.000 0.3190 0.03576 0.02812 -0.0587 0.7811 1.0000
2.250 0.3321 0.03626 0.02858 -0.0576 0.7704 1.0000
2.500 0.3762 0.03628 0.02852 -0.0604 0.7659 1.0000
2.750 0.3921 0.03684 0.02905 -0.0598 0.7548 1.0000
3.000 0.4378 0.03673 0.02889 -0.0627 0.7508 1.0000
3.250 0.4545 0.03734 0.02949 -0.0621 0.7393 1.0000
3.500 0.5018 0.03705 0.02917 -0.0650 0.7356 1.0000
3.750 0.5187 0.03769 0.02982 -0.0645 0.7238 1.0000
4.000 0.5675 0.03718 0.02931 -0.0674 0.7205 1.0000
4.250 0.5846 0.03782 0.02997 -0.0668 0.7083 1.0000
4.500 0.6349 0.03704 0.02920 -0.0696 0.7054 1.0000
4.750 0.6521 0.03767 0.02986 -0.0690 0.6930 1.0000
5.000 0.7031 0.03663 0.02889 -0.0717 0.6904 1.0000
5.250 0.7214 0.03715 0.02945 -0.0710 0.6777 1.0000
5.500 0.7740 0.03572 0.02809 -0.0736 0.6755 1.0000
5.750 0.7929 0.03613 0.02858 -0.0728 0.6628 1.0000
6.000 0.8177 0.03620 0.02872 -0.0726 0.6519 1.0000
6.250 0.8680 0.03445 0.02706 -0.0745 0.6486 1.0000
6.500 0.9250 0.03212 0.02487 -0.0769 0.6469 1.0000
6.750 0.9909 0.02945 0.02236 -0.0806 0.6453 1.0000
7.000 1.0151 0.02917 0.02217 -0.0798 0.6324 1.0000
7.500 1.1082 0.02628 0.01954 -0.0834 0.6119 1.0000
7.750 1.1557 0.02496 0.01832 -0.0855 0.5978 1.0000
8.000 1.1827 0.02459 0.01804 -0.0849 0.5795 1.0000
8.250 1.2142 0.02411 0.01760 -0.0850 0.5596 1.0000
8.500 1.2463 0.02374 0.01723 -0.0852 0.5374 1.0000
8.750 1.2641 0.02394 0.01744 -0.0834 0.5133 1.0000
9.000 1.2820 0.02425 0.01771 -0.0817 0.4881 1.0000
9.250 1.3000 0.02464 0.01800 -0.0801 0.4621 1.0000
9.500 1.3091 0.02538 0.01870 -0.0774 0.4363 1.0000
9.750 1.3174 0.02623 0.01949 -0.0747 0.4107 1.0000
10.000 1.3264 0.02714 0.02029 -0.0722 0.3857 1.0000
10.250 1.3299 0.02827 0.02140 -0.0691 0.3612 1.0000
10.500 1.3342 0.02948 0.02252 -0.0663 0.3375 1.0000
10.750 1.3372 0.03080 0.02378 -0.0635 0.3145 1.0000
11.000 1.3395 0.03225 0.02517 -0.0608 0.2922 1.0000
11.250 1.3406 0.03383 0.02670 -0.0582 0.2707 1.0000
11.500 1.3426 0.03548 0.02826 -0.0558 0.2501 1.0000
11.750 1.3423 0.03732 0.03011 -0.0533 0.2300 1.0000
12.000 1.3424 0.03924 0.03197 -0.0511 0.2112 1.0000
12.250 1.3438 0.04123 0.03383 -0.0491 0.1934 1.0000
12.500 1.3431 0.04341 0.03601 -0.0472 0.1763 1.0000
12.750 1.3429 0.04567 0.03828 -0.0454 0.1605 1.0000
13.000 1.3430 0.04803 0.04063 -0.0438 0.1459 1.0000
13.250 1.3442 0.05043 0.04302 -0.0424 0.1325 1.0000
13.500 1.3459 0.05290 0.04546 -0.0411 0.1203 1.0000
13.750 1.3503 0.05530 0.04781 -0.0401 0.1090 1.0000
14.000 1.3506 0.05797 0.05061 -0.0390 0.0997 1.0000
14.250 1.3550 0.06065 0.05340 -0.0380 0.0910 1.0000
14.500 1.3633 0.06309 0.05578 -0.0373 0.0829 1.0000
14.750 1.3635 0.06603 0.05893 -0.0365 0.0768 1.0000
15.000 1.3727 0.06870 0.06162 -0.0359 0.0705 1.0000
15.250 1.3702 0.07199 0.06516 -0.0353 0.0661 1.0000
15.500 1.3825 0.07466 0.06777 -0.0350 0.0607 1.0000
15.750 1.3739 0.07868 0.07215 -0.0346 0.0580 1.0000
16.000 1.3691 0.08242 0.07612 -0.0345 0.0550 1.0000
16.250 1.3797 0.08552 0.07917 -0.0344 0.0509 1.0000
16.500 1.3629 0.09058 0.08461 -0.0348 0.0497 1.0000
16.750 1.3471 0.09589 0.09026 -0.0358 0.0484 1.0000
17.000 1.3322 0.10138 0.09603 -0.0371 0.0472 1.0000
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Polar data table (+)
Polar graphs
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