EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 200,000 Max Cl/Cd: 50.75 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e541-il-200000-n5.txt Download as CSV file: xf-e541-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 541 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4079 0.08546 0.08197 -0.0847 0.9594 0.0086
-12.000 -0.4461 0.06927 0.06554 -0.0966 0.9504 0.0080
-11.750 -0.4886 0.05767 0.05344 -0.1022 0.9401 0.0076
-11.500 -0.5036 0.05162 0.04694 -0.1041 0.9294 0.0073
-11.250 -0.5083 0.04773 0.04270 -0.1048 0.9185 0.0072
-11.000 -0.5167 0.04394 0.03854 -0.1040 0.9079 0.0073
-10.500 -0.5186 0.03873 0.03266 -0.1008 0.8900 0.0072
-10.250 -0.5133 0.03680 0.03044 -0.0991 0.8833 0.0071
-10.000 -0.5118 0.03414 0.02742 -0.0964 0.8764 0.0072
-9.750 -0.5012 0.03191 0.02486 -0.0949 0.8715 0.0073
-9.500 -0.4861 0.03027 0.02293 -0.0936 0.8666 0.0073
-9.250 -0.4677 0.02851 0.02094 -0.0928 0.8621 0.0075
-9.000 -0.4447 0.02710 0.01929 -0.0925 0.8584 0.0076
-8.750 -0.4221 0.02587 0.01791 -0.0921 0.8549 0.0078
-8.500 -0.4005 0.02486 0.01679 -0.0915 0.8508 0.0083
-8.250 -0.3781 0.02393 0.01574 -0.0909 0.8473 0.0086
-8.000 -0.3565 0.02309 0.01478 -0.0903 0.8442 0.0090
-7.750 -0.3366 0.02226 0.01384 -0.0893 0.8412 0.0098
-7.500 -0.3189 0.02159 0.01305 -0.0881 0.8375 0.0102
-7.250 -0.3022 0.02088 0.01228 -0.0867 0.8339 0.0116
-7.000 -0.2833 0.02040 0.01178 -0.0858 0.8307 0.0143
-6.750 -0.2650 0.01986 0.01112 -0.0846 0.8280 0.0157
-6.500 -0.2513 0.01916 0.01039 -0.0826 0.8244 0.0189
-6.250 -0.2357 0.01861 0.00983 -0.0809 0.8212 0.0260
-6.000 -0.2207 0.01803 0.00930 -0.0791 0.8183 0.0388
-5.750 -0.2072 0.01742 0.00880 -0.0772 0.8157 0.0696
-5.500 -0.1974 0.01671 0.00836 -0.0748 0.8130 0.1231
-5.250 -0.1949 0.01594 0.00797 -0.0711 0.8090 0.1963
-5.000 -0.2007 0.01510 0.00754 -0.0659 0.8051 0.2846
-4.750 -0.2154 0.01428 0.00716 -0.0588 0.8018 0.3817
-4.500 -0.1522 0.01662 0.01090 -0.0605 0.8018 0.6781
-4.250 -0.1574 0.01638 0.01058 -0.0550 0.7989 0.7002
-4.000 -0.1545 0.01635 0.01048 -0.0508 0.7951 0.7185
-3.750 -0.1399 0.01666 0.01068 -0.0483 0.7921 0.7341
-3.500 -0.1209 0.01729 0.01121 -0.0462 0.7898 0.7507
-3.250 -0.0508 0.01953 0.01334 -0.0512 0.7896 0.7586
-3.000 -0.0305 0.01969 0.01340 -0.0498 0.7877 0.7667
-2.750 0.0009 0.01975 0.01334 -0.0506 0.7863 0.7684
-2.250 0.0239 0.01945 0.01293 -0.0456 0.7802 0.7793
-2.000 0.0511 0.01948 0.01290 -0.0457 0.7781 0.7805
-1.750 0.0781 0.01948 0.01283 -0.0458 0.7761 0.7818
-1.500 0.1040 0.01942 0.01270 -0.0457 0.7742 0.7835
-1.250 0.1285 0.01932 0.01254 -0.0455 0.7725 0.7858
-1.000 0.1297 0.01891 0.01209 -0.0416 0.7694 0.7930
-0.750 0.1522 0.01895 0.01212 -0.0409 0.7665 0.7940
-0.500 0.1764 0.01895 0.01210 -0.0405 0.7639 0.7951
-0.250 0.2012 0.01892 0.01204 -0.0402 0.7617 0.7963
0.000 0.2264 0.01883 0.01191 -0.0401 0.7598 0.7977
0.250 0.2523 0.01872 0.01177 -0.0402 0.7581 0.7993
0.500 0.2687 0.01865 0.01171 -0.0386 0.7548 0.8017
0.750 0.2796 0.01844 0.01150 -0.0363 0.7508 0.8058
1.000 0.3018 0.01828 0.01132 -0.0359 0.7479 0.8073
1.250 0.3292 0.01818 0.01122 -0.0361 0.7456 0.8080
1.500 0.3589 0.01807 0.01109 -0.0367 0.7436 0.8088
1.750 0.3743 0.01815 0.01123 -0.0347 0.7387 0.8101
2.000 0.3966 0.01808 0.01119 -0.0341 0.7347 0.8111
2.250 0.4246 0.01790 0.01101 -0.0345 0.7316 0.8120
2.500 0.4563 0.01769 0.01078 -0.0356 0.7291 0.8128
2.750 0.4676 0.01773 0.01092 -0.0329 0.7225 0.8149
3.000 0.4941 0.01755 0.01076 -0.0330 0.7184 0.8162
3.250 0.5262 0.01729 0.01050 -0.0342 0.7153 0.8171
3.500 0.5400 0.01726 0.01054 -0.0322 0.7084 0.8189
3.750 0.5680 0.01702 0.01033 -0.0327 0.7036 0.8200
4.000 0.5926 0.01687 0.01022 -0.0325 0.6981 0.8211
4.250 0.6121 0.01679 0.01023 -0.0311 0.6911 0.8220
4.500 0.6402 0.01659 0.01009 -0.0313 0.6856 0.8227
4.750 0.6557 0.01655 0.01014 -0.0292 0.6770 0.8237
5.000 0.6768 0.01642 0.01008 -0.0282 0.6688 0.8246
5.250 0.7002 0.01623 0.00995 -0.0275 0.6597 0.8254
5.500 0.7140 0.01619 0.01000 -0.0252 0.6480 0.8266
5.750 0.7291 0.01610 0.01000 -0.0230 0.6355 0.8278
6.000 0.7440 0.01599 0.00994 -0.0208 0.6208 0.8290
6.250 0.7621 0.01587 0.00984 -0.0192 0.6021 0.8304
6.500 0.7814 0.01578 0.00972 -0.0178 0.5760 0.8319
6.750 0.8008 0.01578 0.00959 -0.0164 0.5392 0.8331
7.000 0.8138 0.01607 0.00966 -0.0141 0.4956 0.8343
7.250 0.8190 0.01664 0.01004 -0.0106 0.4543 0.8353
7.750 0.8251 0.01810 0.01121 -0.0034 0.3825 0.8376
8.000 0.8286 0.01894 0.01193 -0.0003 0.3497 0.8387
8.250 0.8324 0.01985 0.01271 0.0026 0.3171 0.8400
8.500 0.8375 0.02079 0.01353 0.0052 0.2855 0.8413
8.750 0.8427 0.02179 0.01442 0.0076 0.2538 0.8429
9.000 0.8485 0.02285 0.01535 0.0097 0.2228 0.8443
9.250 0.8545 0.02398 0.01632 0.0117 0.1912 0.8456
9.500 0.8624 0.02507 0.01732 0.0133 0.1629 0.8468
9.750 0.8721 0.02612 0.01828 0.0146 0.1390 0.8479
10.000 0.8826 0.02714 0.01925 0.0159 0.1196 0.8489
10.250 0.8920 0.02819 0.02025 0.0173 0.1009 0.8497
10.500 0.9008 0.02931 0.02132 0.0187 0.0845 0.8507
10.750 0.9104 0.03043 0.02242 0.0200 0.0706 0.8516
11.000 0.9204 0.03156 0.02356 0.0211 0.0600 0.8526
11.250 0.9309 0.03270 0.02475 0.0222 0.0514 0.8537
11.500 0.9401 0.03397 0.02605 0.0233 0.0445 0.8548
11.750 0.9488 0.03531 0.02745 0.0243 0.0381 0.8560
12.000 0.9575 0.03668 0.02890 0.0253 0.0334 0.8574
12.250 0.9662 0.03809 0.03038 0.0262 0.0294 0.8588
12.500 0.9729 0.03972 0.03204 0.0271 0.0257 0.8601
12.750 0.9827 0.04115 0.03360 0.0277 0.0230 0.8613
13.000 0.9903 0.04279 0.03530 0.0283 0.0204 0.8624
13.250 0.9937 0.04480 0.03738 0.0292 0.0181 0.8634
13.500 1.0006 0.04651 0.03925 0.0298 0.0165 0.8644
13.750 1.0072 0.04829 0.04115 0.0304 0.0145 0.8655
14.000 1.0091 0.05060 0.04352 0.0309 0.0130 0.8666
14.250 1.0116 0.05295 0.04601 0.0314 0.0119 0.8678
14.500 1.0148 0.05532 0.04854 0.0316 0.0108 0.8690
14.750 1.0166 0.05792 0.05132 0.0318 0.0101 0.8702
15.000 1.0181 0.06066 0.05419 0.0317 0.0093 0.8715
15.250 1.0177 0.06372 0.05737 0.0314 0.0087 0.8728
15.500 1.0146 0.06720 0.06097 0.0309 0.0083 0.8740
15.750 1.0124 0.07074 0.06467 0.0303 0.0078 0.8752
16.000 1.0116 0.07425 0.06836 0.0294 0.0074 0.8764
16.250 1.0090 0.07800 0.07230 0.0285 0.0070 0.8776
16.500 1.0069 0.08179 0.07626 0.0273 0.0066 0.8789
16.750 1.0048 0.08571 0.08033 0.0257 0.0062 0.8803
17.000 0.9996 0.09026 0.08504 0.0239 0.0059 0.8817
17.250 0.9942 0.09498 0.08991 0.0218 0.0057 0.8831
17.500 0.9880 0.10005 0.09512 0.0193 0.0055 0.8846
17.750 0.9790 0.10570 0.10093 0.0164 0.0054 0.8859
18.000 0.9705 0.11143 0.10683 0.0135 0.0053 0.8871
18.250 0.9592 0.11787 0.11341 0.0100 0.0052 0.8883
18.500 0.9503 0.12402 0.11974 0.0065 0.0053 0.8895
18.750 0.9397 0.13059 0.12647 0.0028 0.0052 0.8907
19.000 0.9276 0.13761 0.13365 -0.0012 0.0052 0.8918
19.250 0.9154 0.14487 0.14106 -0.0055 0.0051 0.8931
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