EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 200,000 Max Cl/Cd: 76.79 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e431-il-200000-n5.txt Download as CSV file: xf-e431-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2274 0.13003 0.12634 -0.0710 0.9813 0.0230
-12.250 -0.2203 0.12538 0.12170 -0.0747 0.9744 0.0231
-12.000 -0.2128 0.12089 0.11722 -0.0780 0.9670 0.0232
-11.750 -0.2037 0.11635 0.11268 -0.0815 0.9607 0.0232
-11.500 -0.1946 0.11183 0.10817 -0.0849 0.9538 0.0232
-11.250 -0.1836 0.10719 0.10352 -0.0887 0.9479 0.0232
-11.000 -0.1716 0.10254 0.09885 -0.0928 0.9423 0.0232
-10.500 -0.1492 0.09094 0.08718 -0.0997 0.9317 0.0125
-10.250 -0.1366 0.08642 0.08264 -0.1043 0.9246 0.0122
-10.000 -0.1237 0.08143 0.07763 -0.1099 0.9176 0.0119
-9.750 -0.1160 0.07539 0.07156 -0.1160 0.9088 0.0116
-9.500 -0.1436 0.05696 0.05302 -0.1321 0.8949 0.0099
-9.250 -0.1512 0.05084 0.04670 -0.1380 0.8817 0.0098
-9.000 -0.1663 0.04629 0.04193 -0.1397 0.8681 0.0097
-8.750 -0.1820 0.04339 0.03883 -0.1381 0.8558 0.0097
-8.500 -0.1944 0.04022 0.03539 -0.1360 0.8466 0.0096
-8.250 -0.1988 0.03728 0.03215 -0.1341 0.8386 0.0095
-8.000 -0.1999 0.03416 0.02866 -0.1321 0.8318 0.0094
-7.750 -0.1961 0.03135 0.02545 -0.1301 0.8251 0.0093
-7.500 -0.1865 0.02853 0.02215 -0.1285 0.8201 0.0093
-7.250 -0.1730 0.02635 0.01958 -0.1270 0.8150 0.0094
-7.000 -0.1565 0.02430 0.01711 -0.1256 0.8098 0.0095
-6.750 -0.1355 0.02276 0.01524 -0.1248 0.8056 0.0096
-6.500 -0.1127 0.02141 0.01358 -0.1241 0.8018 0.0099
-6.250 -0.0921 0.02040 0.01247 -0.1232 0.7972 0.0103
-6.000 -0.0696 0.01960 0.01157 -0.1226 0.7929 0.0107
-5.750 -0.0458 0.01884 0.01068 -0.1222 0.7892 0.0112
-5.500 -0.0218 0.01812 0.00982 -0.1217 0.7858 0.0119
-5.250 0.0002 0.01759 0.00924 -0.1210 0.7813 0.0133
-5.000 0.0239 0.01714 0.00873 -0.1205 0.7774 0.0152
-4.750 0.0480 0.01662 0.00815 -0.1201 0.7738 0.0172
-4.500 0.0737 0.01612 0.00751 -0.1199 0.7708 0.0192
-4.250 0.0963 0.01568 0.00707 -0.1192 0.7666 0.0229
-4.000 0.1200 0.01526 0.00668 -0.1188 0.7626 0.0310
-3.750 0.1448 0.01480 0.00627 -0.1185 0.7590 0.0487
-3.500 0.1704 0.01433 0.00593 -0.1185 0.7559 0.0857
-3.250 0.1947 0.01383 0.00569 -0.1184 0.7524 0.1498
-3.000 0.2171 0.01318 0.00548 -0.1182 0.7483 0.2610
-2.750 0.2394 0.01224 0.00525 -0.1182 0.7445 0.4521
-2.500 0.2600 0.01193 0.00563 -0.1164 0.7413 0.6471
-2.250 0.2876 0.01209 0.00573 -0.1160 0.7386 0.6966
-2.000 0.3112 0.01229 0.00593 -0.1149 0.7344 0.7211
-1.750 0.3364 0.01247 0.00604 -0.1142 0.7304 0.7391
-1.500 0.3625 0.01263 0.00612 -0.1136 0.7269 0.7530
-1.250 0.3878 0.01286 0.00628 -0.1127 0.7238 0.7700
-1.000 0.4097 0.01315 0.00655 -0.1109 0.7203 0.7869
-0.750 0.4325 0.01331 0.00668 -0.1097 0.7160 0.7978
-0.500 0.4580 0.01337 0.00668 -0.1092 0.7122 0.8023
-0.250 0.4865 0.01338 0.00660 -0.1095 0.7088 0.8063
0.000 0.5165 0.01339 0.00651 -0.1102 0.7057 0.8100
0.250 0.5408 0.01343 0.00655 -0.1098 0.7009 0.8127
0.500 0.5668 0.01345 0.00654 -0.1095 0.6967 0.8149
0.750 0.5947 0.01346 0.00649 -0.1097 0.6931 0.8175
1.000 0.6232 0.01349 0.00645 -0.1100 0.6895 0.8201
1.250 0.6480 0.01354 0.00652 -0.1097 0.6843 0.8229
1.500 0.6759 0.01357 0.00651 -0.1100 0.6798 0.8260
1.750 0.7046 0.01357 0.00647 -0.1104 0.6759 0.8283
2.000 0.7290 0.01363 0.00655 -0.1099 0.6710 0.8305
2.250 0.7538 0.01367 0.00661 -0.1095 0.6656 0.8328
2.500 0.7815 0.01368 0.00659 -0.1097 0.6611 0.8351
2.750 0.8077 0.01374 0.00665 -0.1096 0.6560 0.8380
3.000 0.8328 0.01380 0.00675 -0.1094 0.6500 0.8413
3.250 0.8609 0.01382 0.00674 -0.1096 0.6449 0.8437
3.500 0.8839 0.01388 0.00685 -0.1089 0.6387 0.8460
3.750 0.9080 0.01393 0.00692 -0.1083 0.6323 0.8485
4.000 0.9345 0.01396 0.00697 -0.1082 0.6264 0.8511
4.250 0.9570 0.01406 0.00712 -0.1075 0.6188 0.8545
4.500 0.9849 0.01409 0.00713 -0.1077 0.6126 0.8577
4.750 1.0052 0.01420 0.00733 -0.1065 0.6041 0.8607
5.250 1.0499 0.01436 0.00757 -0.1048 0.5879 0.8667
5.500 1.0732 0.01445 0.00768 -0.1041 0.5793 0.8701
5.750 1.0949 0.01458 0.00784 -0.1032 0.5692 0.8739
6.000 1.1133 0.01470 0.00802 -0.1016 0.5588 0.8775
6.250 1.1322 0.01483 0.00817 -0.1000 0.5477 0.8818
6.500 1.1504 0.01500 0.00835 -0.0984 0.5359 0.8865
6.750 1.1656 0.01518 0.00858 -0.0963 0.5230 0.8911
7.000 1.1799 0.01541 0.00883 -0.0940 0.5096 0.8962
7.250 1.1949 0.01570 0.00914 -0.0919 0.4953 0.9021
7.500 1.2074 0.01601 0.00946 -0.0894 0.4801 0.9087
7.750 1.2190 0.01639 0.00984 -0.0868 0.4638 0.9171
8.000 1.2288 0.01680 0.01026 -0.0839 0.4471 0.9272
8.250 1.2379 0.01729 0.01075 -0.0811 0.4294 0.9415
8.750 1.2602 0.01861 0.01201 -0.0772 0.3912 1.0000
9.000 1.2706 0.01949 0.01285 -0.0753 0.3721 1.0000
9.250 1.2789 0.02050 0.01381 -0.0733 0.3525 1.0000
9.500 1.2864 0.02160 0.01485 -0.0712 0.3341 1.0000
9.750 1.2935 0.02276 0.01597 -0.0693 0.3152 1.0000
10.000 1.3005 0.02399 0.01716 -0.0674 0.2973 1.0000
10.250 1.3066 0.02532 0.01845 -0.0655 0.2794 1.0000
10.500 1.3124 0.02672 0.01983 -0.0638 0.2623 1.0000
10.750 1.3179 0.02819 0.02127 -0.0621 0.2459 1.0000
11.000 1.3231 0.02974 0.02279 -0.0604 0.2298 1.0000
11.250 1.3280 0.03135 0.02438 -0.0589 0.2144 1.0000
11.500 1.3328 0.03304 0.02604 -0.0575 0.1993 1.0000
11.750 1.3377 0.03477 0.02778 -0.0561 0.1850 1.0000
12.000 1.3423 0.03658 0.02958 -0.0549 0.1711 1.0000
12.250 1.3468 0.03845 0.03144 -0.0537 0.1581 1.0000
12.500 1.3512 0.04039 0.03338 -0.0527 0.1456 1.0000
12.750 1.3553 0.04242 0.03542 -0.0517 0.1338 1.0000
13.000 1.3587 0.04457 0.03756 -0.0508 0.1226 1.0000
13.250 1.3616 0.04681 0.03982 -0.0500 0.1123 1.0000
13.500 1.3655 0.04904 0.04207 -0.0493 0.1022 1.0000
13.750 1.3693 0.05133 0.04441 -0.0487 0.0932 1.0000
14.000 1.3719 0.05380 0.04691 -0.0482 0.0853 1.0000
14.250 1.3739 0.05639 0.04953 -0.0477 0.0778 1.0000
14.500 1.3770 0.05894 0.05214 -0.0474 0.0708 1.0000
14.750 1.3778 0.06181 0.05505 -0.0472 0.0650 1.0000
15.000 1.3799 0.06459 0.05791 -0.0471 0.0591 1.0000
15.250 1.3804 0.06762 0.06101 -0.0471 0.0543 1.0000
15.500 1.3809 0.07074 0.06420 -0.0472 0.0496 1.0000
15.750 1.3804 0.07406 0.06760 -0.0475 0.0459 1.0000
16.000 1.3803 0.07739 0.07101 -0.0478 0.0420 1.0000
16.250 1.3780 0.08106 0.07476 -0.0483 0.0390 1.0000
16.500 1.3777 0.08456 0.07839 -0.0489 0.0360 1.0000
16.750 1.3739 0.08863 0.08252 -0.0498 0.0336 1.0000
17.000 1.3725 0.09243 0.08646 -0.0507 0.0312 1.0000
17.250 1.3698 0.09646 0.09060 -0.0517 0.0292 1.0000
17.500 1.3640 0.10105 0.09527 -0.0531 0.0276 1.0000
17.750 1.3622 0.10506 0.09943 -0.0544 0.0257 1.0000
18.000 1.3586 0.10944 0.10393 -0.0559 0.0241 1.0000
18.250 1.3524 0.11430 0.10887 -0.0578 0.0230 1.0000
18.500 1.3486 0.11880 0.11351 -0.0596 0.0217 1.0000
18.750 1.3448 0.12335 0.11820 -0.0616 0.0205 1.0000
19.000 1.3396 0.12821 0.12317 -0.0639 0.0194 1.0000
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Polar data table (+)
Polar graphs
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