EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 200,000 Max Cl/Cd: 68.17 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1200-il-200000-n5.txt Download as CSV file: xf-e1200-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1200 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5157 0.06618 0.06165 -0.1031 0.9621 0.0210
-13.250 -0.5326 0.05815 0.05330 -0.1117 0.9483 0.0210
-13.000 -0.5401 0.05202 0.04682 -0.1186 0.9354 0.0210
-12.750 -0.5389 0.04723 0.04172 -0.1240 0.9232 0.0210
-12.500 -0.5322 0.04352 0.03774 -0.1279 0.9108 0.0212
-12.250 -0.5234 0.04077 0.03478 -0.1302 0.8983 0.0214
-12.000 -0.5165 0.03838 0.03216 -0.1314 0.8868 0.0216
-11.750 -0.5083 0.03644 0.03002 -0.1319 0.8766 0.0218
-11.500 -0.5026 0.03474 0.02812 -0.1313 0.8668 0.0219
-11.250 -0.4943 0.03324 0.02641 -0.1306 0.8591 0.0222
-11.000 -0.4870 0.03186 0.02487 -0.1293 0.8514 0.0224
-10.750 -0.4772 0.03060 0.02344 -0.1281 0.8453 0.0227
-10.500 -0.4663 0.02942 0.02208 -0.1268 0.8400 0.0230
-10.250 -0.4553 0.02835 0.02087 -0.1253 0.8345 0.0235
-10.000 -0.4422 0.02736 0.01972 -0.1239 0.8297 0.0239
-9.500 -0.4130 0.02570 0.01773 -0.1212 0.8209 0.0250
-9.250 -0.3958 0.02483 0.01677 -0.1202 0.8166 0.0256
-9.000 -0.3779 0.02400 0.01591 -0.1193 0.8131 0.0261
-8.750 -0.3592 0.02328 0.01514 -0.1184 0.8101 0.0266
-8.500 -0.3411 0.02260 0.01441 -0.1174 0.8069 0.0273
-8.250 -0.3233 0.02197 0.01373 -0.1163 0.8032 0.0278
-8.000 -0.3050 0.02136 0.01306 -0.1152 0.7996 0.0286
-7.750 -0.2860 0.02078 0.01240 -0.1142 0.7964 0.0293
-7.500 -0.2662 0.02023 0.01175 -0.1133 0.7937 0.0301
-7.250 -0.2478 0.01965 0.01116 -0.1123 0.7910 0.0312
-7.000 -0.2286 0.01920 0.01071 -0.1113 0.7879 0.0328
-6.750 -0.2084 0.01877 0.01024 -0.1105 0.7849 0.0344
-6.500 -0.1874 0.01834 0.00975 -0.1097 0.7820 0.0361
-6.250 -0.1661 0.01787 0.00926 -0.1090 0.7793 0.0382
-6.000 -0.1432 0.01748 0.00880 -0.1085 0.7770 0.0413
-5.750 -0.1207 0.01707 0.00840 -0.1079 0.7748 0.0462
-5.500 -0.0993 0.01670 0.00808 -0.1072 0.7720 0.0555
-5.250 -0.0775 0.01629 0.00776 -0.1066 0.7692 0.0727
-5.000 -0.0548 0.01589 0.00747 -0.1061 0.7664 0.0974
-4.750 -0.0309 0.01553 0.00720 -0.1058 0.7639 0.1250
-4.500 -0.0065 0.01515 0.00693 -0.1057 0.7617 0.1599
-4.250 0.0182 0.01473 0.00667 -0.1057 0.7599 0.2056
-4.000 0.0402 0.01415 0.00644 -0.1054 0.7576 0.2824
-3.750 0.0599 0.01342 0.00627 -0.1048 0.7546 0.4003
-3.500 0.0816 0.01305 0.00646 -0.1039 0.7517 0.5246
-3.250 0.1077 0.01313 0.00665 -0.1034 0.7493 0.5762
-3.000 0.1355 0.01324 0.00673 -0.1033 0.7472 0.6033
-2.750 0.1638 0.01337 0.00681 -0.1032 0.7452 0.6231
-2.500 0.1928 0.01348 0.00684 -0.1034 0.7434 0.6379
-2.250 0.2200 0.01361 0.00690 -0.1033 0.7409 0.6505
-2.000 0.2451 0.01379 0.00709 -0.1027 0.7381 0.6597
-1.750 0.2716 0.01393 0.00719 -0.1024 0.7353 0.6697
-1.500 0.2985 0.01408 0.00732 -0.1021 0.7326 0.6803
-1.250 0.3257 0.01424 0.00747 -0.1018 0.7303 0.6901
-1.000 0.3548 0.01435 0.00750 -0.1020 0.7283 0.6999
-0.750 0.3838 0.01442 0.00754 -0.1021 0.7264 0.7050
-0.500 0.4072 0.01456 0.00771 -0.1013 0.7227 0.7098
-0.250 0.4331 0.01463 0.00776 -0.1011 0.7191 0.7147
0.000 0.4610 0.01465 0.00773 -0.1013 0.7158 0.7187
0.250 0.4897 0.01463 0.00769 -0.1014 0.7129 0.7212
0.500 0.5204 0.01458 0.00759 -0.1019 0.7102 0.7242
0.750 0.5429 0.01466 0.00771 -0.1011 0.7048 0.7276
1.000 0.5697 0.01464 0.00766 -0.1010 0.6999 0.7310
1.500 0.6253 0.01450 0.00747 -0.1010 0.6897 0.7370
1.750 0.6503 0.01445 0.00743 -0.1004 0.6831 0.7395
2.000 0.6803 0.01432 0.00726 -0.1007 0.6783 0.7423
2.250 0.7028 0.01437 0.00736 -0.0999 0.6715 0.7457
2.500 0.7296 0.01434 0.00731 -0.0998 0.6656 0.7491
2.750 0.7585 0.01427 0.00722 -0.1000 0.6605 0.7520
3.000 0.7796 0.01434 0.00737 -0.0988 0.6530 0.7544
3.250 0.8066 0.01428 0.00731 -0.0987 0.6471 0.7572
3.500 0.8287 0.01434 0.00743 -0.0977 0.6390 0.7606
3.750 0.8550 0.01430 0.00739 -0.0974 0.6315 0.7639
4.000 0.8774 0.01436 0.00749 -0.0966 0.6221 0.7673
4.250 0.9017 0.01434 0.00748 -0.0959 0.6129 0.7700
4.500 0.9226 0.01438 0.00755 -0.0947 0.6014 0.7730
4.750 0.9435 0.01443 0.00763 -0.0934 0.5883 0.7766
5.000 0.9646 0.01449 0.00768 -0.0922 0.5730 0.7803
5.250 0.9854 0.01457 0.00770 -0.0910 0.5549 0.7841
5.500 1.0021 0.01470 0.00777 -0.0889 0.5334 0.7871
5.750 1.0149 0.01491 0.00789 -0.0862 0.5087 0.7909
6.000 1.0257 0.01526 0.00813 -0.0832 0.4830 0.7954
6.500 1.0418 0.01636 0.00897 -0.0768 0.4318 0.8043
6.750 1.0484 0.01702 0.00954 -0.0736 0.4094 0.8089
7.000 1.0561 0.01773 0.01017 -0.0708 0.3882 0.8142
7.250 1.0639 0.01846 0.01084 -0.0681 0.3689 0.8196
7.500 1.0715 0.01923 0.01156 -0.0654 0.3513 0.8253
7.750 1.0806 0.02003 0.01232 -0.0632 0.3353 0.8318
8.000 1.0897 0.02084 0.01310 -0.0610 0.3203 0.8378
8.250 1.0994 0.02168 0.01392 -0.0589 0.3068 0.8447
8.500 1.1093 0.02255 0.01477 -0.0571 0.2944 0.8523
8.750 1.1207 0.02334 0.01558 -0.0553 0.2831 0.8615
9.000 1.1315 0.02417 0.01642 -0.0536 0.2724 0.8723
9.250 1.1409 0.02506 0.01733 -0.0517 0.2627 0.8864
9.500 1.1526 0.02580 0.01814 -0.0501 0.2534 0.9068
10.000 1.1779 0.02749 0.01987 -0.0480 0.2362 1.0000
10.250 1.1918 0.02850 0.02088 -0.0472 0.2286 1.0000
10.500 1.2060 0.02949 0.02188 -0.0465 0.2210 1.0000
10.750 1.2189 0.03057 0.02294 -0.0457 0.2140 1.0000
11.000 1.2331 0.03158 0.02398 -0.0450 0.2068 1.0000
11.250 1.2444 0.03278 0.02515 -0.0441 0.2005 1.0000
11.500 1.2592 0.03378 0.02622 -0.0434 0.1939 1.0000
11.750 1.2707 0.03501 0.02744 -0.0426 0.1877 1.0000
12.000 1.2836 0.03615 0.02863 -0.0420 0.1820 1.0000
12.250 1.2960 0.03735 0.02987 -0.0413 0.1760 1.0000
12.500 1.3057 0.03878 0.03129 -0.0405 0.1708 1.0000
12.750 1.3192 0.03994 0.03254 -0.0399 0.1650 1.0000
13.000 1.3298 0.04134 0.03397 -0.0393 0.1596 1.0000
13.250 1.3393 0.04285 0.03550 -0.0386 0.1548 1.0000
13.500 1.3512 0.04420 0.03694 -0.0381 0.1494 1.0000
13.750 1.3598 0.04585 0.03862 -0.0375 0.1443 1.0000
14.000 1.3690 0.04748 0.04030 -0.0370 0.1399 1.0000
14.250 1.3793 0.04905 0.04195 -0.0366 0.1349 1.0000
14.500 1.3861 0.05096 0.04389 -0.0361 0.1303 1.0000
14.750 1.3940 0.05281 0.04580 -0.0357 0.1260 1.0000
15.000 1.4025 0.05464 0.04772 -0.0354 0.1213 1.0000
15.250 1.4079 0.05681 0.04994 -0.0351 0.1171 1.0000
15.500 1.4134 0.05901 0.05220 -0.0349 0.1132 1.0000
15.750 1.4207 0.06107 0.05437 -0.0348 0.1090 1.0000
16.000 1.4247 0.06354 0.05690 -0.0348 0.1051 1.0000
16.250 1.4265 0.06629 0.05968 -0.0348 0.1017 1.0000
16.500 1.4331 0.06855 0.06208 -0.0349 0.0982 1.0000
16.750 1.4361 0.07128 0.06490 -0.0351 0.0945 1.0000
17.000 1.4362 0.07444 0.06812 -0.0355 0.0913 1.0000
17.250 1.4380 0.07742 0.07119 -0.0359 0.0883 1.0000
17.500 1.4402 0.08044 0.07434 -0.0364 0.0846 1.0000
17.750 1.4393 0.08390 0.07788 -0.0372 0.0815 1.0000
18.000 1.4350 0.08789 0.08192 -0.0381 0.0788 1.0000
18.250 1.4361 0.09123 0.08540 -0.0390 0.0756 1.0000
18.500 1.4341 0.09505 0.08934 -0.0402 0.0725 1.0000
18.750 1.4287 0.09944 0.09380 -0.0417 0.0697 1.0000
19.000 1.4232 0.10390 0.09833 -0.0434 0.0674 1.0000
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