EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 500,000 Max Cl/Cd: 78.33 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e541-il-500000.txt Download as CSV file: xf-e541-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.2559 0.14424 0.14214 -0.0566 0.9905 0.0157
-15.750 -0.2508 0.14114 0.13903 -0.0597 0.9827 0.0158
-8.500 -0.4805 0.02629 0.02024 -0.0812 0.8356 0.0112
-8.250 -0.4326 0.02285 0.01658 -0.0852 0.8342 0.0098
-8.000 -0.3846 0.02049 0.01394 -0.0884 0.8330 0.0091
-7.750 -0.3489 0.01909 0.01236 -0.0895 0.8311 0.0089
-7.500 -0.3237 0.01825 0.01139 -0.0892 0.8287 0.0088
-7.250 -0.3036 0.01749 0.01056 -0.0881 0.8260 0.0089
-7.000 -0.2859 0.01682 0.00985 -0.0867 0.8230 0.0094
-6.750 -0.2687 0.01626 0.00924 -0.0852 0.8201 0.0097
-6.500 -0.2520 0.01570 0.00860 -0.0836 0.8172 0.0103
-6.250 -0.2380 0.01502 0.00783 -0.0815 0.8146 0.0119
-6.000 -0.2212 0.01459 0.00737 -0.0800 0.8121 0.0138
-5.750 -0.2073 0.01402 0.00680 -0.0778 0.8093 0.0227
-5.500 -0.1985 0.01330 0.00634 -0.0750 0.8065 0.0672
-5.250 -0.1878 0.01271 0.00597 -0.0725 0.8039 0.1163
-5.000 -0.1871 0.01188 0.00553 -0.0683 0.8013 0.2037
-4.750 -0.2023 0.01109 0.00517 -0.0611 0.7980 0.3022
-4.500 -0.2151 0.01014 0.00473 -0.0543 0.7946 0.4217
-4.250 -0.2316 0.00870 0.00433 -0.0466 0.7915 0.6366
-4.000 -0.2055 0.00935 0.00516 -0.0456 0.7897 0.7272
-3.750 -0.1760 0.00989 0.00561 -0.0456 0.7881 0.7425
-3.500 -0.1455 0.01054 0.00619 -0.0457 0.7865 0.7537
-3.250 -0.1142 0.01123 0.00683 -0.0459 0.7849 0.7608
-3.000 -0.0850 0.01180 0.00739 -0.0457 0.7832 0.7669
-2.750 -0.0466 0.01305 0.00865 -0.0464 0.7817 0.7710
-2.500 -0.0116 0.01419 0.00976 -0.0465 0.7799 0.7803
-2.250 0.0363 0.01537 0.01093 -0.0488 0.7786 0.7818
-2.000 0.0677 0.01553 0.01105 -0.0495 0.7769 0.7831
-1.750 0.0735 0.01498 0.01042 -0.0468 0.7746 0.7929
-1.500 0.1036 0.01499 0.01038 -0.0473 0.7731 0.7935
-1.250 0.1338 0.01503 0.01037 -0.0479 0.7716 0.7941
-1.000 0.1606 0.01506 0.01040 -0.0479 0.7697 0.7949
-0.750 0.1869 0.01507 0.01041 -0.0478 0.7675 0.7958
-0.500 0.2132 0.01506 0.01039 -0.0478 0.7652 0.7969
-0.250 0.2393 0.01501 0.01033 -0.0477 0.7631 0.7983
0.000 0.2651 0.01492 0.01022 -0.0477 0.7610 0.8000
0.250 0.2891 0.01471 0.00997 -0.0477 0.7589 0.8025
0.500 0.3062 0.01420 0.00939 -0.0471 0.7563 0.8074
0.750 0.3303 0.01413 0.00937 -0.0465 0.7530 0.8081
1.000 0.3563 0.01405 0.00930 -0.0464 0.7498 0.8088
1.250 0.3838 0.01392 0.00915 -0.0466 0.7468 0.8094
1.500 0.4133 0.01380 0.00900 -0.0473 0.7440 0.8101
1.750 0.4374 0.01375 0.00898 -0.0469 0.7405 0.8111
2.000 0.4617 0.01363 0.00889 -0.0465 0.7366 0.8122
2.250 0.4884 0.01345 0.00871 -0.0468 0.7332 0.8131
2.500 0.5179 0.01328 0.00852 -0.0475 0.7300 0.8141
2.750 0.5415 0.01315 0.00842 -0.0472 0.7257 0.8157
3.000 0.5666 0.01294 0.00823 -0.0472 0.7211 0.8169
3.250 0.5958 0.01272 0.00800 -0.0480 0.7172 0.8180
3.500 0.6228 0.01253 0.00783 -0.0485 0.7127 0.8191
3.750 0.6490 0.01233 0.00766 -0.0489 0.7070 0.8207
4.000 0.6773 0.01213 0.00745 -0.0492 0.7021 0.8213
4.250 0.7002 0.01198 0.00738 -0.0485 0.6959 0.8218
4.500 0.7262 0.01181 0.00724 -0.0484 0.6896 0.8224
4.750 0.7502 0.01167 0.00716 -0.0479 0.6825 0.8230
5.000 0.7749 0.01152 0.00704 -0.0475 0.6745 0.8235
5.250 0.7966 0.01140 0.00700 -0.0466 0.6643 0.8242
5.500 0.8187 0.01129 0.00693 -0.0456 0.6524 0.8250
5.750 0.8395 0.01121 0.00688 -0.0445 0.6377 0.8259
6.000 0.8585 0.01115 0.00681 -0.0429 0.6177 0.8269
6.250 0.8742 0.01116 0.00677 -0.0408 0.5894 0.8278
6.500 0.8837 0.01132 0.00681 -0.0375 0.5512 0.8289
6.750 0.8822 0.01163 0.00692 -0.0321 0.5085 0.8302
7.000 0.8786 0.01214 0.00722 -0.0266 0.4648 0.8316
7.250 0.8758 0.01289 0.00774 -0.0216 0.4198 0.8330
7.500 0.8764 0.01369 0.00834 -0.0175 0.3786 0.8342
7.750 0.8779 0.01445 0.00895 -0.0137 0.3413 0.8354
8.000 0.8809 0.01524 0.00960 -0.0103 0.3067 0.8364
8.250 0.8847 0.01611 0.01031 -0.0071 0.2718 0.8373
8.500 0.8904 0.01698 0.01104 -0.0045 0.2393 0.8382
8.750 0.8976 0.01784 0.01179 -0.0021 0.2098 0.8391
9.000 0.9061 0.01870 0.01255 0.0000 0.1827 0.8400
9.250 0.9152 0.01958 0.01332 0.0019 0.1569 0.8409
9.500 0.9245 0.02049 0.01413 0.0037 0.1338 0.8419
9.750 0.9339 0.02143 0.01496 0.0054 0.1115 0.8428
10.000 0.9440 0.02237 0.01581 0.0069 0.0911 0.8438
10.250 0.9533 0.02338 0.01673 0.0085 0.0731 0.8448
10.500 0.9628 0.02443 0.01770 0.0100 0.0575 0.8460
10.750 0.9725 0.02550 0.01872 0.0114 0.0451 0.8470
11.000 0.9819 0.02663 0.01979 0.0128 0.0357 0.8478
11.250 0.9944 0.02758 0.02078 0.0138 0.0309 0.8485
11.500 1.0019 0.02882 0.02204 0.0153 0.0263 0.8494
11.750 1.0156 0.02965 0.02295 0.0161 0.0237 0.8502
12.000 1.0252 0.03080 0.02412 0.0173 0.0207 0.8511
12.250 1.0318 0.03222 0.02561 0.0187 0.0180 0.8520
12.500 1.0440 0.03325 0.02672 0.0195 0.0158 0.8529
12.750 1.0476 0.03498 0.02845 0.0209 0.0124 0.8538
13.000 1.0594 0.03612 0.02968 0.0216 0.0108 0.8548
13.250 1.0664 0.03768 0.03127 0.0225 0.0090 0.8558
13.500 1.0620 0.04028 0.03399 0.0242 0.0080 0.8568
13.750 1.0702 0.04187 0.03569 0.0248 0.0075 0.8578
14.000 1.0782 0.04351 0.03743 0.0254 0.0066 0.8589
14.250 1.0839 0.04540 0.03940 0.0259 0.0061 0.8600
14.500 1.0865 0.04766 0.04175 0.0265 0.0057 0.8612
14.750 1.0857 0.05035 0.04453 0.0270 0.0054 0.8621
15.000 1.0753 0.05415 0.04849 0.0278 0.0051 0.8629
15.250 1.0730 0.05719 0.05167 0.0281 0.0050 0.8638
15.500 1.0768 0.05964 0.05425 0.0280 0.0048 0.8648
15.750 1.0758 0.06276 0.05752 0.0279 0.0047 0.8657
16.000 1.0744 0.06602 0.06093 0.0276 0.0046 0.8667
16.250 1.0719 0.06954 0.06460 0.0271 0.0045 0.8676
16.500 1.0687 0.07330 0.06851 0.0264 0.0045 0.8686
16.750 1.0647 0.07731 0.07268 0.0253 0.0043 0.8695
17.000 1.0581 0.08183 0.07738 0.0240 0.0043 0.8704
17.250 1.0527 0.08632 0.08202 0.0224 0.0043 0.8713
17.500 1.0447 0.09143 0.08729 0.0204 0.0042 0.8722
17.750 1.0351 0.09696 0.09300 0.0181 0.0042 0.8731
18.000 1.0253 0.10268 0.09889 0.0154 0.0042 0.8739
18.250 1.0125 0.10917 0.10557 0.0122 0.0042 0.8746
18.500 1.0007 0.11569 0.11225 0.0087 0.0043 0.8753
18.750 0.9871 0.12276 0.11948 0.0047 0.0043 0.8760
19.000 0.9710 0.13056 0.12746 0.0002 0.0043 0.8766
19.250 0.9559 0.13837 0.13543 -0.0044 0.0043 0.8774
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