EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 100,000 Max Cl/Cd: 50.73 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e434-il-100000-n5.txt Download as CSV file: xf-e434-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 434 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1451 0.11734 0.11277 -0.0698 0.9623 0.0445
-11.250 -0.1418 0.11364 0.10906 -0.0735 0.9584 0.0447
-11.000 -0.1391 0.10986 0.10529 -0.0765 0.9519 0.0449
-10.750 -0.1349 0.10568 0.10111 -0.0800 0.9469 0.0450
-10.500 -0.1280 0.10134 0.09677 -0.0832 0.9423 0.0451
-10.250 -0.1128 0.09674 0.09215 -0.0835 0.9362 0.0456
-10.000 -0.1031 0.09243 0.08783 -0.0859 0.9314 0.0458
-9.750 -0.0981 0.08799 0.08338 -0.0889 0.9259 0.0457
-9.000 -0.1746 0.08521 0.08041 -0.0900 0.9334 0.0248
-8.750 -0.1559 0.08228 0.07743 -0.0919 0.9285 0.0235
-8.250 -0.1527 0.06974 0.06485 -0.1050 0.9069 0.0200
-8.000 -0.1490 0.06561 0.06067 -0.1088 0.8980 0.0197
-7.750 -0.1516 0.06242 0.05740 -0.1100 0.8871 0.0193
-7.500 -0.1520 0.05841 0.05327 -0.1117 0.8787 0.0190
-7.250 -0.1522 0.05468 0.04938 -0.1124 0.8700 0.0187
-7.000 -0.1498 0.05107 0.04557 -0.1125 0.8628 0.0181
-6.750 -0.1479 0.04729 0.04153 -0.1118 0.8552 0.0177
-6.500 -0.1412 0.04319 0.03705 -0.1113 0.8498 0.0172
-6.250 -0.1356 0.04019 0.03372 -0.1094 0.8423 0.0172
-6.000 -0.1213 0.03764 0.03080 -0.1086 0.8374 0.0179
-5.750 -0.1072 0.03498 0.02770 -0.1073 0.8323 0.0186
-5.500 -0.0928 0.03256 0.02477 -0.1055 0.8263 0.0193
-5.250 -0.0724 0.03007 0.02166 -0.1044 0.8221 0.0202
-5.000 -0.0486 0.02838 0.01969 -0.1040 0.8186 0.0207
-4.750 -0.0298 0.02705 0.01813 -0.1025 0.8127 0.0214
-4.500 -0.0055 0.02567 0.01649 -0.1018 0.8085 0.0221
-4.250 0.0216 0.02429 0.01485 -0.1014 0.8052 0.0232
-4.000 0.0449 0.02324 0.01359 -0.1004 0.8009 0.0248
-3.750 0.0658 0.02264 0.01300 -0.0994 0.7957 0.0278
-3.500 0.0902 0.02187 0.01214 -0.0988 0.7918 0.0320
-3.250 0.1166 0.02112 0.01124 -0.0984 0.7888 0.0369
-3.000 0.1356 0.02065 0.01082 -0.0970 0.7835 0.0464
-2.750 0.1570 0.02004 0.01029 -0.0959 0.7788 0.0690
-2.500 0.1806 0.01919 0.00982 -0.0953 0.7753 0.1453
-2.250 0.2011 0.01790 0.00948 -0.0945 0.7725 0.3753
-2.000 0.2027 0.01728 0.01028 -0.0882 0.7662 0.7105
-1.750 0.2185 0.01759 0.01057 -0.0844 0.7619 0.8228
-1.500 0.2402 0.01781 0.01063 -0.0819 0.7587 0.8695
-1.250 0.2638 0.01804 0.01070 -0.0800 0.7550 0.9021
-1.000 0.2981 0.01833 0.01084 -0.0805 0.7502 0.9317
-0.750 0.4095 0.01828 0.01043 -0.0961 0.7496 0.9656
-0.500 0.4542 0.01822 0.01019 -0.0997 0.7461 0.9745
-0.250 0.4933 0.01811 0.00991 -0.1022 0.7430 0.9796
0.000 0.5243 0.01818 0.00988 -0.1034 0.7384 0.9848
0.250 0.5556 0.01827 0.00990 -0.1047 0.7331 0.9894
0.500 0.5880 0.01824 0.00977 -0.1060 0.7291 0.9935
0.750 0.6226 0.01814 0.00957 -0.1076 0.7260 0.9967
1.000 0.6425 0.01845 0.00988 -0.1069 0.7192 1.0000
1.250 0.6612 0.01855 0.00993 -0.1055 0.7143 1.0000
1.500 0.6852 0.01851 0.00982 -0.1048 0.7108 1.0000
1.750 0.6914 0.01892 0.01027 -0.1014 0.7033 1.0000
2.000 0.7104 0.01899 0.01031 -0.0999 0.6984 1.0000
2.250 0.7358 0.01892 0.01017 -0.0994 0.6949 1.0000
2.500 0.7363 0.01940 0.01072 -0.0949 0.6865 1.0000
2.750 0.7578 0.01939 0.01067 -0.0938 0.6819 1.0000
3.000 0.7681 0.01963 0.01093 -0.0908 0.6755 1.0000
3.250 0.7799 0.01980 0.01111 -0.0881 0.6690 1.0000
3.500 0.8066 0.01967 0.01096 -0.0878 0.6649 1.0000
3.750 0.8066 0.02013 0.01147 -0.0831 0.6562 1.0000
4.000 0.8321 0.02004 0.01137 -0.0827 0.6512 1.0000
4.250 0.8442 0.02035 0.01171 -0.0801 0.6436 1.0000
4.500 0.8676 0.02036 0.01177 -0.0794 0.6373 1.0000
4.750 0.8881 0.02048 0.01192 -0.0783 0.6304 1.0000
5.000 0.9088 0.02060 0.01208 -0.0772 0.6228 1.0000
5.250 0.9314 0.02068 0.01219 -0.0763 0.6155 1.0000
5.500 0.9527 0.02077 0.01236 -0.0753 0.6073 1.0000
5.750 0.9719 0.02095 0.01259 -0.0740 0.5985 1.0000
6.000 0.9992 0.02084 0.01253 -0.0738 0.5906 1.0000
6.250 1.0134 0.02117 0.01295 -0.0718 0.5800 1.0000
6.500 1.0366 0.02120 0.01304 -0.0710 0.5705 1.0000
6.750 1.0601 0.02121 0.01310 -0.0703 0.5603 1.0000
7.000 1.0734 0.02152 0.01349 -0.0680 0.5482 1.0000
7.250 1.0898 0.02175 0.01380 -0.0662 0.5359 1.0000
7.500 1.1078 0.02196 0.01406 -0.0647 0.5231 1.0000
7.750 1.1252 0.02219 0.01435 -0.0631 0.5092 1.0000
8.000 1.1414 0.02250 0.01471 -0.0614 0.4941 1.0000
8.250 1.1564 0.02288 0.01513 -0.0596 0.4779 1.0000
8.500 1.1709 0.02332 0.01560 -0.0578 0.4607 1.0000
8.750 1.1849 0.02382 0.01610 -0.0560 0.4426 1.0000
9.000 1.1983 0.02439 0.01667 -0.0541 0.4238 1.0000
9.250 1.2078 0.02519 0.01748 -0.0520 0.4040 1.0000
9.500 1.2170 0.02605 0.01832 -0.0499 0.3835 1.0000
9.750 1.2259 0.02700 0.01922 -0.0479 0.3637 1.0000
10.000 1.2323 0.02814 0.02036 -0.0458 0.3433 1.0000
10.250 1.2384 0.02936 0.02158 -0.0438 0.3235 1.0000
10.500 1.2438 0.03069 0.02286 -0.0419 0.3045 1.0000
10.750 1.2487 0.03212 0.02430 -0.0401 0.2857 1.0000
11.000 1.2529 0.03366 0.02584 -0.0383 0.2673 1.0000
11.250 1.2565 0.03531 0.02748 -0.0367 0.2497 1.0000
11.500 1.2591 0.03708 0.02925 -0.0351 0.2326 1.0000
11.750 1.2615 0.03894 0.03111 -0.0336 0.2164 1.0000
12.000 1.2632 0.04092 0.03309 -0.0323 0.2006 1.0000
12.250 1.2650 0.04298 0.03517 -0.0311 0.1854 1.0000
12.500 1.2664 0.04516 0.03737 -0.0300 0.1709 1.0000
12.750 1.2671 0.04746 0.03969 -0.0290 0.1574 1.0000
13.000 1.2673 0.04991 0.04215 -0.0282 0.1448 1.0000
13.250 1.2681 0.05241 0.04472 -0.0275 0.1327 1.0000
13.500 1.2685 0.05502 0.04739 -0.0270 0.1213 1.0000
13.750 1.2685 0.05775 0.05018 -0.0265 0.1112 1.0000
14.000 1.2674 0.06070 0.05317 -0.0262 0.1022 1.0000
14.250 1.2654 0.06384 0.05636 -0.0261 0.0939 1.0000
14.500 1.2650 0.06690 0.05953 -0.0260 0.0858 1.0000
14.750 1.2616 0.07040 0.06305 -0.0262 0.0795 1.0000
15.000 1.2604 0.07375 0.06654 -0.0264 0.0729 1.0000
15.250 1.2567 0.07747 0.07031 -0.0269 0.0678 1.0000
15.500 1.2547 0.08109 0.07409 -0.0274 0.0624 1.0000
15.750 1.2493 0.08521 0.07822 -0.0282 0.0587 1.0000
16.000 1.2482 0.08889 0.08209 -0.0289 0.0542 1.0000
16.250 1.2438 0.09310 0.08639 -0.0300 0.0509 1.0000
16.500 1.2404 0.09717 0.09056 -0.0311 0.0478 1.0000
16.750 1.2378 0.10125 0.09480 -0.0323 0.0446 1.0000
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Polar data table (+)
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