EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 200,000 Max Cl/Cd: 61.24 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e546-il-200000.txt Download as CSV file: xf-e546-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 546 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3615 0.09009 0.08691 -0.0561 1.0000 0.0618
-11.000 -0.3962 0.08044 0.07726 -0.0620 1.0000 0.0622
-10.750 -0.4264 0.07392 0.07070 -0.0643 1.0000 0.0622
-10.500 -0.5476 0.07365 0.07009 -0.0644 1.0000 0.0556
-10.250 -0.5656 0.07047 0.06688 -0.0633 1.0000 0.0559
-10.000 -0.5857 0.06774 0.06412 -0.0612 1.0000 0.0563
-9.750 -0.6091 0.06563 0.06199 -0.0576 1.0000 0.0566
-9.500 -0.6414 0.06452 0.06089 -0.0515 1.0000 0.0565
-9.250 -0.6782 0.06417 0.06054 -0.0437 1.0000 0.0562
-9.000 -0.6806 0.06157 0.05786 -0.0429 0.9963 0.0576
-8.000 -0.6300 0.03414 0.02746 -0.0439 0.9622 0.0256
-7.750 -0.5937 0.03073 0.02377 -0.0460 0.9590 0.0244
-7.500 -0.5571 0.02790 0.02059 -0.0473 0.9546 0.0237
-7.250 -0.5181 0.02579 0.01824 -0.0490 0.9500 0.0237
-7.000 -0.4748 0.02400 0.01634 -0.0515 0.9472 0.0246
-6.750 -0.4305 0.02253 0.01473 -0.0543 0.9448 0.0262
-6.500 -0.3946 0.02104 0.01337 -0.0564 0.9394 0.0290
-6.250 -0.3616 0.01980 0.01216 -0.0582 0.9317 0.0350
-6.000 -0.3336 0.01848 0.01085 -0.0592 0.9227 0.0418
-5.750 -0.3102 0.01701 0.00949 -0.0595 0.9127 0.0661
-5.250 -0.3131 0.01324 0.00733 -0.0525 0.8828 0.3571
-5.000 -0.3075 0.01308 0.00839 -0.0474 0.8708 0.6219
-4.750 -0.2752 0.01419 0.00934 -0.0467 0.8630 0.6660
-4.500 -0.2459 0.01562 0.01069 -0.0448 0.8526 0.6866
-4.250 -0.2088 0.01708 0.01204 -0.0440 0.8456 0.7012
-4.000 -0.1814 0.01786 0.01271 -0.0426 0.8352 0.7126
-3.750 -0.1448 0.01898 0.01370 -0.0421 0.8274 0.7216
-3.500 -0.1030 0.02039 0.01503 -0.0416 0.8190 0.7311
-3.250 -0.0544 0.02185 0.01634 -0.0423 0.8123 0.7449
-3.000 -0.0127 0.02235 0.01673 -0.0433 0.8030 0.7503
-2.750 -0.0068 0.02188 0.01615 -0.0404 0.7931 0.7594
-2.500 0.0283 0.02190 0.01605 -0.0412 0.7846 0.7617
-2.250 0.0566 0.02182 0.01587 -0.0412 0.7760 0.7650
-2.000 0.0527 0.02112 0.01506 -0.0372 0.7667 0.7740
-1.750 0.0826 0.02104 0.01491 -0.0373 0.7580 0.7757
-1.500 0.1131 0.02092 0.01468 -0.0377 0.7506 0.7777
-1.250 0.1365 0.02076 0.01447 -0.0370 0.7421 0.7805
-1.000 0.1561 0.02046 0.01407 -0.0361 0.7345 0.7841
-0.750 0.1592 0.01983 0.01338 -0.0335 0.7260 0.7898
-0.500 0.1870 0.01966 0.01314 -0.0334 0.7190 0.7912
-0.250 0.2118 0.01952 0.01295 -0.0330 0.7116 0.7928
0.000 0.2364 0.01933 0.01271 -0.0327 0.7042 0.7945
0.250 0.2603 0.01917 0.01249 -0.0324 0.6976 0.7967
0.500 0.2808 0.01891 0.01221 -0.0317 0.6900 0.7987
0.750 0.3056 0.01868 0.01188 -0.0319 0.6843 0.8010
1.000 0.3238 0.01839 0.01159 -0.0312 0.6763 0.8036
1.250 0.3491 0.01811 0.01123 -0.0318 0.6703 0.8055
1.500 0.3731 0.01801 0.01115 -0.0312 0.6635 0.8067
1.750 0.3982 0.01790 0.01103 -0.0310 0.6568 0.8080
2.000 0.4260 0.01781 0.01087 -0.0314 0.6514 0.8091
2.250 0.4484 0.01771 0.01083 -0.0308 0.6439 0.8104
2.500 0.4759 0.01761 0.01069 -0.0312 0.6381 0.8118
2.750 0.5003 0.01757 0.01068 -0.0311 0.6317 0.8138
3.000 0.5261 0.01748 0.01059 -0.0312 0.6249 0.8155
3.250 0.5553 0.01742 0.01048 -0.0321 0.6194 0.8169
3.500 0.5790 0.01735 0.01048 -0.0320 0.6116 0.8185
3.750 0.6088 0.01727 0.01035 -0.0330 0.6055 0.8199
4.000 0.6334 0.01724 0.01039 -0.0329 0.5980 0.8215
4.250 0.6594 0.01717 0.01033 -0.0328 0.5911 0.8230
4.500 0.6844 0.01718 0.01038 -0.0325 0.5842 0.8244
4.750 0.7098 0.01715 0.01040 -0.0324 0.5766 0.8258
5.000 0.7369 0.01715 0.01042 -0.0326 0.5698 0.8272
5.250 0.7613 0.01713 0.01047 -0.0323 0.5614 0.8289
5.500 0.7887 0.01712 0.01048 -0.0326 0.5539 0.8305
5.750 0.8135 0.01709 0.01052 -0.0324 0.5448 0.8323
6.000 0.8398 0.01710 0.01056 -0.0326 0.5363 0.8343
6.250 0.8668 0.01708 0.01058 -0.0329 0.5271 0.8366
6.500 0.8887 0.01707 0.01067 -0.0319 0.5176 0.8383
6.750 0.9147 0.01705 0.01065 -0.0318 0.5085 0.8399
7.000 0.9347 0.01703 0.01077 -0.0306 0.4971 0.8419
7.250 0.9566 0.01704 0.01086 -0.0297 0.4856 0.8440
7.500 0.9790 0.01704 0.01091 -0.0290 0.4735 0.8462
7.750 1.0008 0.01706 0.01098 -0.0282 0.4603 0.8486
8.000 1.0211 0.01711 0.01107 -0.0272 0.4454 0.8511
8.250 1.0381 0.01716 0.01121 -0.0255 0.4292 0.8536
8.500 1.0521 0.01724 0.01139 -0.0232 0.4112 0.8565
8.750 1.0649 0.01739 0.01160 -0.0208 0.3908 0.8597
9.000 1.0756 0.01765 0.01183 -0.0181 0.3686 0.8631
9.250 1.0826 0.01798 0.01215 -0.0150 0.3429 0.8667
9.500 1.0857 0.01847 0.01260 -0.0112 0.3166 0.8703
9.750 1.0866 0.01918 0.01323 -0.0073 0.2897 0.8745
10.000 1.0869 0.02008 0.01404 -0.0038 0.2629 0.8794
10.250 1.0872 0.02110 0.01500 -0.0006 0.2373 0.8844
10.500 1.0842 0.02225 0.01608 0.0029 0.2156 0.8903
10.750 1.0842 0.02351 0.01731 0.0055 0.1934 0.8974
11.000 1.0818 0.02490 0.01867 0.0083 0.1745 0.9049
11.250 1.0802 0.02650 0.02023 0.0105 0.1567 0.9139
11.500 1.0792 0.02809 0.02185 0.0125 0.1398 0.9254
12.000 1.0838 0.03210 0.02591 0.0133 0.1082 1.0000
12.250 1.0861 0.03450 0.02826 0.0132 0.0954 1.0000
12.500 1.0875 0.03700 0.03073 0.0131 0.0846 1.0000
12.750 1.0869 0.03968 0.03337 0.0132 0.0759 1.0000
13.000 1.0877 0.04228 0.03595 0.0131 0.0683 1.0000
13.250 1.0899 0.04478 0.03850 0.0131 0.0617 1.0000
13.500 1.0879 0.04768 0.04132 0.0131 0.0565 1.0000
13.750 1.0923 0.05010 0.04386 0.0129 0.0514 1.0000
14.000 1.0913 0.05296 0.04665 0.0129 0.0475 1.0000
14.250 1.0954 0.05551 0.04934 0.0125 0.0435 1.0000
14.500 1.0953 0.05837 0.05212 0.0123 0.0401 1.0000
14.750 1.0985 0.06114 0.05505 0.0118 0.0370 1.0000
15.000 1.0992 0.06412 0.05803 0.0112 0.0342 1.0000
15.250 1.1015 0.06700 0.06100 0.0109 0.0317 1.0000
15.500 1.1007 0.07037 0.06443 0.0098 0.0289 1.0000
15.750 1.1032 0.07321 0.06729 0.0095 0.0269 1.0000
16.000 1.1020 0.07685 0.07109 0.0083 0.0247 1.0000
16.250 1.1050 0.07969 0.07387 0.0077 0.0230 1.0000
16.500 1.1014 0.08384 0.07824 0.0063 0.0212 1.0000
16.750 1.1005 0.08755 0.08203 0.0048 0.0198 1.0000
17.000 1.1046 0.09029 0.08471 0.0043 0.0186 1.0000
17.250 1.0999 0.09487 0.08956 0.0026 0.0176 1.0000
17.500 1.0970 0.09912 0.09397 0.0009 0.0167 1.0000
17.750 1.0958 0.10305 0.09798 -0.0008 0.0160 1.0000
18.000 1.1023 0.10551 0.10038 -0.0011 0.0152 1.0000
18.250 1.0920 0.11129 0.10643 -0.0041 0.0149 1.0000
18.500 1.0800 0.11757 0.11297 -0.0074 0.0146 1.0000
18.750 1.0701 0.12353 0.11914 -0.0107 0.0144 1.0000
19.000 1.0574 0.13022 0.12605 -0.0145 0.0142 1.0000
19.250 1.0449 0.13707 0.13310 -0.0187 0.0139 1.0000
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