EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 200,000 Max Cl/Cd: 80.78 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e434-il-200000-n5.txt Download as CSV file: xf-e434-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1184 0.07068 0.06674 -0.1062 0.8627 0.0127
-8.500 -0.1172 0.06734 0.06336 -0.1082 0.8526 0.0124
-8.250 -0.1198 0.06365 0.05966 -0.1108 0.8426 0.0122
-8.000 -0.1301 0.05947 0.05541 -0.1132 0.8332 0.0120
-7.750 -0.1392 0.05601 0.05187 -0.1137 0.8246 0.0116
-7.500 -0.1636 0.04625 0.04176 -0.1144 0.8172 0.0100
-7.250 -0.1614 0.04331 0.03865 -0.1136 0.8107 0.0099
-7.000 -0.1553 0.04052 0.03563 -0.1127 0.8055 0.0098
-6.750 -0.1494 0.03712 0.03196 -0.1115 0.8003 0.0096
-6.500 -0.1412 0.03374 0.02825 -0.1100 0.7951 0.0094
-6.250 -0.1302 0.03038 0.02446 -0.1084 0.7907 0.0093
-6.000 -0.1157 0.02736 0.02094 -0.1069 0.7868 0.0091
-5.750 -0.0987 0.02477 0.01790 -0.1054 0.7820 0.0091
-5.500 -0.0781 0.02268 0.01538 -0.1043 0.7779 0.0091
-5.250 -0.0551 0.02091 0.01319 -0.1034 0.7745 0.0094
-5.000 -0.0309 0.01960 0.01159 -0.1027 0.7711 0.0096
-4.750 -0.0070 0.01847 0.01022 -0.1019 0.7667 0.0100
-4.500 0.0170 0.01765 0.00932 -0.1014 0.7628 0.0105
-4.250 0.0420 0.01702 0.00859 -0.1010 0.7595 0.0115
-4.000 0.0676 0.01651 0.00798 -0.1007 0.7564 0.0137
-3.750 0.0916 0.01603 0.00746 -0.1001 0.7522 0.0153
-3.500 0.1159 0.01547 0.00683 -0.0995 0.7482 0.0170
-3.250 0.1412 0.01503 0.00630 -0.0991 0.7448 0.0193
-3.000 0.1672 0.01461 0.00583 -0.0988 0.7418 0.0251
-2.750 0.1913 0.01416 0.00546 -0.0982 0.7379 0.0417
-2.500 0.2153 0.01368 0.00520 -0.0978 0.7339 0.0896
-2.250 0.2388 0.01310 0.00499 -0.0975 0.7303 0.1876
-2.000 0.2605 0.01226 0.00480 -0.0969 0.7271 0.3711
-1.750 0.2757 0.01129 0.00486 -0.0946 0.7236 0.6399
-1.500 0.2931 0.01134 0.00524 -0.0915 0.7194 0.7811
-1.250 0.3161 0.01148 0.00533 -0.0900 0.7156 0.8201
-1.000 0.3397 0.01161 0.00537 -0.0887 0.7124 0.8449
-0.750 0.3631 0.01173 0.00541 -0.0873 0.7091 0.8631
-0.500 0.3831 0.01187 0.00553 -0.0853 0.7046 0.8816
-0.250 0.4004 0.01203 0.00566 -0.0822 0.7006 0.9065
0.000 0.4236 0.01211 0.00568 -0.0804 0.6972 0.9264
0.250 0.4507 0.01213 0.00560 -0.0802 0.6939 0.9340
0.500 0.4778 0.01216 0.00559 -0.0802 0.6891 0.9379
0.750 0.5050 0.01216 0.00553 -0.0802 0.6848 0.9417
1.000 0.5313 0.01216 0.00544 -0.0801 0.6812 0.9458
1.250 0.5608 0.01218 0.00543 -0.0807 0.6769 0.9482
1.500 0.5892 0.01221 0.00544 -0.0810 0.6717 0.9512
1.750 0.6181 0.01221 0.00539 -0.0815 0.6674 0.9543
2.000 0.6462 0.01223 0.00535 -0.0817 0.6632 0.9575
2.250 0.6730 0.01227 0.00543 -0.0818 0.6573 0.9609
2.500 0.7042 0.01229 0.00541 -0.0827 0.6522 0.9634
2.750 0.7346 0.01232 0.00541 -0.0835 0.6474 0.9662
3.000 0.7618 0.01237 0.00550 -0.0837 0.6408 0.9699
3.250 0.7915 0.01239 0.00549 -0.0844 0.6355 0.9729
3.500 0.8221 0.01246 0.00559 -0.0853 0.6289 0.9757
3.750 0.8528 0.01250 0.00565 -0.0862 0.6224 0.9791
4.000 0.8823 0.01256 0.00571 -0.0869 0.6157 0.9832
4.250 0.9134 0.01263 0.00582 -0.0880 0.6078 0.9864
4.500 0.9441 0.01270 0.00592 -0.0889 0.6000 0.9901
4.750 0.9739 0.01277 0.00600 -0.0897 0.5913 0.9948
5.000 0.9995 0.01287 0.00616 -0.0897 0.5820 1.0000
5.250 1.0151 0.01295 0.00622 -0.0875 0.5736 1.0000
5.500 1.0313 0.01308 0.00639 -0.0855 0.5635 1.0000
5.750 1.0508 0.01322 0.00656 -0.0842 0.5530 1.0000
6.000 1.0716 0.01337 0.00671 -0.0831 0.5417 1.0000
6.250 1.0924 0.01356 0.00689 -0.0821 0.5292 1.0000
6.500 1.1124 0.01377 0.00711 -0.0809 0.5152 1.0000
6.750 1.1317 0.01403 0.00737 -0.0797 0.4999 1.0000
7.000 1.1499 0.01432 0.00764 -0.0782 0.4833 1.0000
7.250 1.1667 0.01465 0.00796 -0.0765 0.4653 1.0000
7.500 1.1811 0.01503 0.00832 -0.0744 0.4466 1.0000
7.750 1.1929 0.01548 0.00871 -0.0719 0.4273 1.0000
8.000 1.2034 0.01602 0.00919 -0.0692 0.4072 1.0000
8.250 1.2132 0.01663 0.00976 -0.0666 0.3862 1.0000
8.500 1.2214 0.01735 0.01042 -0.0639 0.3656 1.0000
8.750 1.2294 0.01813 0.01115 -0.0613 0.3453 1.0000
9.000 1.2370 0.01899 0.01197 -0.0588 0.3255 1.0000
9.250 1.2433 0.01997 0.01289 -0.0562 0.3061 1.0000
9.500 1.2498 0.02101 0.01389 -0.0539 0.2880 1.0000
9.750 1.2565 0.02211 0.01497 -0.0518 0.2693 1.0000
10.000 1.2625 0.02331 0.01614 -0.0497 0.2512 1.0000
10.250 1.2674 0.02464 0.01743 -0.0476 0.2329 1.0000
10.500 1.2722 0.02604 0.01879 -0.0457 0.2158 1.0000
10.750 1.2776 0.02747 0.02020 -0.0440 0.1990 1.0000
11.000 1.2830 0.02896 0.02167 -0.0424 0.1831 1.0000
11.250 1.2881 0.03051 0.02322 -0.0408 0.1680 1.0000
11.500 1.2931 0.03213 0.02483 -0.0394 0.1539 1.0000
11.750 1.2978 0.03383 0.02651 -0.0381 0.1403 1.0000
12.000 1.3022 0.03559 0.02827 -0.0368 0.1277 1.0000
12.250 1.3062 0.03745 0.03013 -0.0356 0.1155 1.0000
12.500 1.3098 0.03939 0.03207 -0.0345 0.1047 1.0000
12.750 1.3139 0.04134 0.03406 -0.0336 0.0944 1.0000
13.000 1.3182 0.04335 0.03610 -0.0327 0.0849 1.0000
13.250 1.3215 0.04550 0.03829 -0.0319 0.0766 1.0000
13.500 1.3235 0.04785 0.04066 -0.0312 0.0694 1.0000
13.750 1.3273 0.05008 0.04296 -0.0307 0.0622 1.0000
14.000 1.3295 0.05255 0.04548 -0.0302 0.0566 1.0000
14.250 1.3313 0.05512 0.04811 -0.0298 0.0511 1.0000
14.500 1.3331 0.05777 0.05086 -0.0295 0.0464 1.0000
14.750 1.3332 0.06068 0.05382 -0.0294 0.0421 1.0000
15.000 1.3341 0.06359 0.05684 -0.0294 0.0385 1.0000
15.250 1.3340 0.06668 0.06001 -0.0295 0.0353 1.0000
15.500 1.3321 0.07009 0.06350 -0.0297 0.0326 1.0000
15.750 1.3324 0.07330 0.06684 -0.0301 0.0300 1.0000
16.000 1.3294 0.07704 0.07066 -0.0307 0.0279 1.0000
16.250 1.3272 0.08076 0.07449 -0.0314 0.0260 1.0000
16.500 1.3254 0.08449 0.07836 -0.0322 0.0241 1.0000
16.750 1.3209 0.08869 0.08266 -0.0332 0.0227 1.0000
17.000 1.3156 0.09313 0.08722 -0.0345 0.0214 1.0000
17.250 1.3129 0.09725 0.09149 -0.0357 0.0200 1.0000
17.500 1.3086 0.10168 0.09606 -0.0373 0.0188 1.0000
17.750 1.3014 0.10668 0.10115 -0.0392 0.0179 1.0000
18.000 1.2958 0.11150 0.10611 -0.0410 0.0170 1.0000
18.250 1.2916 0.11616 0.11092 -0.0430 0.0159 1.0000
18.500 1.2859 0.12113 0.11603 -0.0452 0.0152 1.0000
18.750 1.2792 0.12637 0.12138 -0.0477 0.0144 1.0000
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