EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 200,000 Max Cl/Cd: 82.03 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e434-il-200000.txt Download as CSV file: xf-e434-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1071 0.10510 0.10187 -0.0778 0.9679 0.0357
-10.750 -0.1092 0.10083 0.09761 -0.0830 0.9636 0.0366
-10.500 -0.1062 0.09628 0.09306 -0.0881 0.9602 0.0369
-10.250 -0.0903 0.09103 0.08781 -0.0895 0.9574 0.0375
-10.000 -0.0729 0.08752 0.08428 -0.0902 0.9511 0.0386
-9.750 -0.0601 0.08348 0.08022 -0.0928 0.9466 0.0399
-9.500 -0.0498 0.07926 0.07599 -0.0960 0.9420 0.0414
-9.250 -0.0455 0.07503 0.07175 -0.0991 0.9346 0.0430
-9.000 -0.0484 0.06990 0.06661 -0.1055 0.9288 0.0445
-8.750 -0.0571 0.06533 0.06204 -0.1105 0.9186 0.0449
-8.500 -0.0701 0.06007 0.05673 -0.1166 0.9093 0.0450
-8.250 -0.0504 0.05693 0.05362 -0.1118 0.9042 0.0462
-8.000 -0.0404 0.05429 0.05094 -0.1112 0.8983 0.0475
-7.750 -0.0453 0.05089 0.04754 -0.1129 0.8895 0.0481
-7.500 -0.0545 0.04723 0.04382 -0.1149 0.8822 0.0490
-7.250 -0.0670 0.04439 0.04095 -0.1147 0.8730 0.0496
-7.000 -0.0717 0.04100 0.03743 -0.1152 0.8670 0.0509
-6.750 -0.0858 0.03791 0.03401 -0.1153 0.8582 0.0542
-6.500 -0.0909 0.03337 0.02920 -0.1143 0.8527 0.0556
-6.250 -0.0773 0.03046 0.02638 -0.1139 0.8484 0.0569
-6.000 -0.0665 0.02828 0.02416 -0.1130 0.8425 0.0588
-5.750 -0.0555 0.02578 0.02145 -0.1121 0.8379 0.0631
-5.500 -0.0484 0.02255 0.01785 -0.1109 0.8334 0.0683
-5.250 -0.0338 0.02068 0.01598 -0.1100 0.8279 0.0709
-5.000 -0.0157 0.02799 0.02136 -0.1119 0.8354 0.0299
-4.750 0.0014 0.02458 0.01738 -0.1096 0.8298 0.0251
-4.500 0.0254 0.02306 0.01561 -0.1087 0.8252 0.0243
-4.250 0.0517 0.02142 0.01369 -0.1081 0.8218 0.0242
-4.000 0.0788 0.02008 0.01209 -0.1075 0.8187 0.0250
-3.750 0.0996 0.01933 0.01140 -0.1066 0.8131 0.0270
-3.500 0.1247 0.01862 0.01060 -0.1059 0.8089 0.0311
-3.250 0.1506 0.01778 0.00976 -0.1055 0.8056 0.0339
-3.000 0.1738 0.01706 0.00902 -0.1045 0.8018 0.0386
-2.750 0.1944 0.01660 0.00864 -0.1033 0.7964 0.0534
-2.500 0.2136 0.01520 0.00790 -0.1021 0.7923 0.1876
-2.250 0.2226 0.01330 0.00785 -0.0990 0.7891 0.6386
-2.000 0.2305 0.01372 0.00870 -0.0932 0.7841 0.8249
-1.750 0.2438 0.01415 0.00910 -0.0890 0.7792 0.8666
-1.500 0.2621 0.01441 0.00925 -0.0856 0.7756 0.8946
-1.250 0.2866 0.01458 0.00926 -0.0835 0.7730 0.9186
-1.000 0.3254 0.01487 0.00945 -0.0848 0.7684 0.9384
-0.750 0.4023 0.01497 0.00935 -0.0941 0.7656 0.9543
-0.500 0.4997 0.01483 0.00899 -0.1077 0.7635 0.9747
-0.250 0.5628 0.01460 0.00861 -0.1151 0.7605 0.9863
0.000 0.6078 0.01441 0.00829 -0.1189 0.7575 0.9924
0.250 0.6445 0.01439 0.00825 -0.1214 0.7520 0.9976
0.500 0.6743 0.01436 0.00817 -0.1223 0.7470 1.0000
0.750 0.6980 0.01433 0.00806 -0.1217 0.7431 1.0000
1.000 0.7169 0.01447 0.00819 -0.1204 0.7378 1.0000
1.250 0.7358 0.01456 0.00827 -0.1191 0.7320 1.0000
1.500 0.7598 0.01450 0.00816 -0.1185 0.7278 1.0000
1.750 0.7788 0.01462 0.00827 -0.1172 0.7224 1.0000
2.000 0.7972 0.01471 0.00837 -0.1157 0.7163 1.0000
2.250 0.8219 0.01463 0.00824 -0.1152 0.7121 1.0000
2.500 0.8387 0.01478 0.00842 -0.1134 0.7060 1.0000
2.750 0.8581 0.01483 0.00848 -0.1120 0.7000 1.0000
3.000 0.8840 0.01472 0.00831 -0.1116 0.6958 1.0000
3.250 0.8966 0.01494 0.00859 -0.1091 0.6886 1.0000
3.500 0.9187 0.01487 0.00852 -0.1081 0.6829 1.0000
3.750 0.9406 0.01486 0.00849 -0.1070 0.6777 1.0000
4.000 0.9539 0.01498 0.00868 -0.1045 0.6701 1.0000
4.250 0.9802 0.01481 0.00847 -0.1042 0.6652 1.0000
4.500 0.9898 0.01498 0.00872 -0.1009 0.6570 1.0000
4.750 1.0131 0.01484 0.00857 -0.1000 0.6510 1.0000
5.000 1.0247 0.01493 0.00873 -0.0971 0.6431 1.0000
5.250 1.0459 0.01482 0.00861 -0.0958 0.6362 1.0000
5.500 1.0586 0.01488 0.00873 -0.0930 0.6279 1.0000
5.750 1.0830 0.01474 0.00859 -0.0923 0.6204 1.0000
6.000 1.0990 0.01482 0.00874 -0.0903 0.6107 1.0000
6.250 1.1243 0.01475 0.00867 -0.0898 0.6019 1.0000
6.500 1.1462 0.01474 0.00871 -0.0888 0.5913 1.0000
6.750 1.1664 0.01480 0.00882 -0.0875 0.5794 1.0000
7.000 1.1881 0.01485 0.00891 -0.0865 0.5672 1.0000
7.250 1.2093 0.01492 0.00902 -0.0854 0.5539 1.0000
7.500 1.2294 0.01504 0.00917 -0.0841 0.5393 1.0000
7.750 1.2476 0.01521 0.00936 -0.0825 0.5230 1.0000
8.000 1.2645 0.01543 0.00958 -0.0806 0.5051 1.0000
8.250 1.2799 0.01572 0.00985 -0.0786 0.4861 1.0000
8.500 1.2919 0.01609 0.01020 -0.0760 0.4663 1.0000
8.750 1.3002 0.01653 0.01063 -0.0727 0.4456 1.0000
9.000 1.3079 0.01711 0.01112 -0.0696 0.4246 1.0000
9.250 1.3137 0.01778 0.01177 -0.0663 0.4023 1.0000
9.500 1.3183 0.01860 0.01251 -0.0630 0.3804 1.0000
9.750 1.3219 0.01952 0.01338 -0.0598 0.3580 1.0000
10.000 1.3242 0.02060 0.01439 -0.0566 0.3362 1.0000
10.250 1.3264 0.02178 0.01552 -0.0537 0.3146 1.0000
10.500 1.3280 0.02309 0.01677 -0.0510 0.2934 1.0000
10.750 1.3288 0.02455 0.01817 -0.0483 0.2738 1.0000
11.000 1.3310 0.02603 0.01963 -0.0461 0.2536 1.0000
11.250 1.3322 0.02766 0.02122 -0.0439 0.2347 1.0000
11.500 1.3325 0.02944 0.02293 -0.0418 0.2167 1.0000
11.750 1.3335 0.03126 0.02472 -0.0399 0.1991 1.0000
12.000 1.3347 0.03315 0.02659 -0.0383 0.1818 1.0000
12.250 1.3353 0.03516 0.02857 -0.0367 0.1656 1.0000
12.500 1.3356 0.03727 0.03067 -0.0352 0.1506 1.0000
12.750 1.3355 0.03950 0.03289 -0.0339 0.1364 1.0000
13.000 1.3352 0.04184 0.03522 -0.0327 0.1231 1.0000
13.250 1.3347 0.04430 0.03767 -0.0316 0.1111 1.0000
13.500 1.3338 0.04688 0.04025 -0.0307 0.1003 1.0000
13.750 1.3314 0.04969 0.04304 -0.0298 0.0906 1.0000
14.000 1.3297 0.05255 0.04589 -0.0292 0.0821 1.0000
14.250 1.3300 0.05528 0.04871 -0.0287 0.0739 1.0000
14.500 1.3271 0.05843 0.05185 -0.0282 0.0674 1.0000
14.750 1.3263 0.06145 0.05495 -0.0280 0.0614 1.0000
15.000 1.3248 0.06461 0.05816 -0.0277 0.0563 1.0000
15.250 1.3243 0.06777 0.06139 -0.0278 0.0517 1.0000
15.500 1.3226 0.07106 0.06472 -0.0277 0.0478 1.0000
15.750 1.3229 0.07428 0.06806 -0.0280 0.0441 1.0000
16.000 1.3208 0.07762 0.07132 -0.0280 0.0408 1.0000
16.250 1.3213 0.08102 0.07495 -0.0286 0.0381 1.0000
16.500 1.3205 0.08455 0.07855 -0.0292 0.0355 1.0000
16.750 1.3205 0.08780 0.08180 -0.0295 0.0330 1.0000
17.000 1.3192 0.09162 0.08584 -0.0304 0.0308 1.0000
17.250 1.3182 0.09530 0.08959 -0.0314 0.0289 1.0000
17.500 1.3184 0.09860 0.09290 -0.0319 0.0268 1.0000
17.750 1.3144 0.10304 0.09757 -0.0334 0.0252 1.0000
18.000 1.3122 0.10711 0.10174 -0.0348 0.0236 1.0000
18.250 1.3150 0.10995 0.10452 -0.0353 0.0219 1.0000
18.500 1.3076 0.11518 0.11002 -0.0375 0.0209 1.0000
18.750 1.3016 0.12015 0.11518 -0.0399 0.0197 1.0000
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Polar data table (+)
Polar graphs
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