EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 541 AIRFOIL (e541-il) Reynolds number: 100,000 Max Cl/Cd: 29.34 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e541-il-100000-n5.txt Download as CSV file: xf-e541-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4101 0.11114 0.10628 -0.0645 1.0000 0.0159
-12.500 -0.4198 0.10709 0.10233 -0.0649 1.0000 0.0157
-12.250 -0.4326 0.10253 0.09785 -0.0655 0.9991 0.0155
-12.000 -0.4358 0.09332 0.08863 -0.0725 0.9915 0.0153
-11.750 -0.4482 0.08424 0.07946 -0.0799 0.9838 0.0151
-11.500 -0.4606 0.07758 0.07271 -0.0851 0.9758 0.0148
-11.250 -0.4749 0.07135 0.06631 -0.0894 0.9694 0.0146
-11.000 -0.4916 0.06585 0.06057 -0.0917 0.9616 0.0146
-10.750 -0.5020 0.06096 0.05540 -0.0936 0.9560 0.0145
-10.500 -0.5110 0.05702 0.05119 -0.0938 0.9481 0.0143
-10.250 -0.5141 0.05327 0.04711 -0.0941 0.9422 0.0141
-10.000 -0.5211 0.04988 0.04337 -0.0924 0.9335 0.0142
-9.750 -0.5205 0.04660 0.03964 -0.0912 0.9277 0.0143
-9.500 -0.5212 0.04427 0.03698 -0.0886 0.9197 0.0142
-9.250 -0.5143 0.04166 0.03394 -0.0867 0.9145 0.0147
-9.000 -0.5058 0.03952 0.03144 -0.0846 0.9086 0.0149
-8.750 -0.4913 0.03757 0.02903 -0.0831 0.9035 0.0157
-8.500 -0.4687 0.03517 0.02637 -0.0833 0.9004 0.0171
-8.250 -0.4436 0.03350 0.02450 -0.0836 0.8971 0.0182
-8.000 -0.4117 0.03174 0.02253 -0.0846 0.8941 0.0190
-7.750 -0.3734 0.02998 0.02055 -0.0862 0.8923 0.0206
-7.500 -0.3412 0.02869 0.01907 -0.0870 0.8899 0.0220
-7.250 -0.3155 0.02749 0.01780 -0.0870 0.8872 0.0250
-7.000 -0.2925 0.02662 0.01687 -0.0867 0.8844 0.0297
-6.750 -0.2800 0.02608 0.01620 -0.0844 0.8790 0.0325
-6.500 -0.2644 0.02523 0.01536 -0.0827 0.8749 0.0409
-6.250 -0.2454 0.02440 0.01456 -0.0816 0.8720 0.0579
-6.000 -0.2303 0.02367 0.01415 -0.0798 0.8686 0.1001
-5.750 -0.2214 0.02299 0.01406 -0.0770 0.8641 0.1963
-5.500 -0.2024 0.02286 0.01601 -0.0732 0.8619 0.5458
-5.000 -0.1537 0.02573 0.01873 -0.0683 0.8566 0.6965
-4.750 -0.1403 0.02681 0.01967 -0.0649 0.8520 0.7153
-4.500 -0.1275 0.02761 0.02033 -0.0616 0.8481 0.7328
-4.250 -0.0959 0.02883 0.02134 -0.0609 0.8459 0.7528
-4.000 -0.0429 0.02991 0.02220 -0.0640 0.8452 0.7684
-3.750 -0.0269 0.02998 0.02212 -0.0621 0.8426 0.7789
-3.500 0.0051 0.03011 0.02211 -0.0630 0.8399 0.7823
-3.000 0.0321 0.03033 0.02213 -0.0587 0.8323 0.7948
-2.750 0.0645 0.03020 0.02186 -0.0600 0.8303 0.7979
-2.500 0.0575 0.03036 0.02197 -0.0541 0.8259 0.8067
-2.250 0.0808 0.03050 0.02204 -0.0538 0.8222 0.8092
-2.000 0.1051 0.03049 0.02194 -0.0536 0.8191 0.8123
-1.750 0.1217 0.03042 0.02180 -0.0521 0.8163 0.8169
-1.500 0.1327 0.03029 0.02159 -0.0495 0.8140 0.8218
-1.250 0.1360 0.03078 0.02209 -0.0456 0.8076 0.8252
-1.000 0.1510 0.03082 0.02207 -0.0437 0.8041 0.8287
-0.750 0.1440 0.03071 0.02191 -0.0377 0.8005 0.8350
-0.500 0.1458 0.03119 0.02241 -0.0335 0.7939 0.8378
-0.250 0.1624 0.03123 0.02241 -0.0320 0.7902 0.8403
0.000 0.1818 0.03108 0.02222 -0.0309 0.7876 0.8431
0.500 0.1589 0.03144 0.02256 -0.0175 0.7747 0.8515
0.750 0.1900 0.03123 0.02232 -0.0186 0.7728 0.8529
1.250 0.1678 0.03134 0.02242 -0.0055 0.7593 0.8609
1.500 0.1873 0.03099 0.02204 -0.0044 0.7569 0.8628
1.750 0.1716 0.03147 0.02255 0.0026 0.7466 0.8656
2.000 0.2037 0.03121 0.02228 0.0015 0.7446 0.8666
2.500 0.2157 0.03128 0.02237 0.0079 0.7316 0.8707
2.750 0.2483 0.03090 0.02200 0.0069 0.7297 0.8718
3.250 0.2644 0.03080 0.02193 0.0124 0.7163 0.8760
4.000 0.3279 0.03046 0.02173 0.0146 0.7001 0.8793
4.250 0.3333 0.03074 0.02206 0.0175 0.6900 0.8812
4.500 0.3689 0.03022 0.02160 0.0163 0.6876 0.8817
5.000 0.4091 0.02993 0.02147 0.0180 0.6737 0.8840
5.250 0.4165 0.03021 0.02182 0.0204 0.6623 0.8856
5.500 0.4437 0.02982 0.02151 0.0204 0.6567 0.8867
5.750 0.4626 0.02970 0.02147 0.0214 0.6476 0.8884
6.250 0.5114 0.02899 0.02099 0.0221 0.6322 0.8906
6.500 0.5256 0.02908 0.02118 0.0237 0.6200 0.8918
6.750 0.5430 0.02903 0.02125 0.0249 0.6080 0.8929
7.000 0.5634 0.02884 0.02118 0.0257 0.5959 0.8940
7.250 0.5855 0.02860 0.02109 0.0264 0.5831 0.8951
7.500 0.6080 0.02833 0.02094 0.0271 0.5686 0.8963
7.750 0.6332 0.02795 0.02066 0.0275 0.5525 0.8976
8.000 0.6640 0.02722 0.02003 0.0275 0.5343 0.8988
8.250 0.6923 0.02670 0.01959 0.0277 0.5098 0.9002
8.500 0.7248 0.02602 0.01887 0.0275 0.4784 0.9013
8.750 0.7499 0.02588 0.01861 0.0280 0.4403 0.9024
9.000 0.7682 0.02618 0.01877 0.0290 0.4006 0.9037
9.250 0.7805 0.02678 0.01924 0.0307 0.3636 0.9050
9.500 0.7897 0.02760 0.01994 0.0325 0.3272 0.9064
9.750 0.7975 0.02856 0.02079 0.0342 0.2928 0.9080
10.000 0.8046 0.02965 0.02179 0.0359 0.2590 0.9097
10.250 0.8119 0.03080 0.02284 0.0373 0.2274 0.9114
10.500 0.8189 0.03205 0.02399 0.0386 0.1974 0.9133
10.750 0.8260 0.03337 0.02521 0.0399 0.1690 0.9154
11.250 0.8391 0.03616 0.02784 0.0422 0.1214 0.9194
11.500 0.8465 0.03757 0.02923 0.0433 0.1027 0.9214
11.750 0.8535 0.03908 0.03074 0.0442 0.0879 0.9233
12.000 0.8601 0.04071 0.03239 0.0451 0.0755 0.9253
12.250 0.8664 0.04242 0.03413 0.0459 0.0654 0.9274
12.500 0.8708 0.04434 0.03609 0.0466 0.0578 0.9295
13.000 0.8799 0.04831 0.04021 0.0479 0.0472 0.9339
13.250 0.8880 0.05010 0.04221 0.0484 0.0425 0.9363
13.500 0.8926 0.05222 0.04443 0.0487 0.0383 0.9391
13.750 0.8961 0.05457 0.04685 0.0490 0.0353 0.9420
14.000 0.9033 0.05668 0.04918 0.0492 0.0320 0.9452
14.250 0.9073 0.05907 0.05171 0.0490 0.0291 0.9489
14.500 0.9083 0.06192 0.05462 0.0488 0.0269 0.9528
14.750 0.9142 0.06452 0.05745 0.0485 0.0249 0.9571
15.000 0.9176 0.06747 0.06065 0.0477 0.0225 0.9617
15.250 0.9189 0.07072 0.06406 0.0465 0.0208 0.9673
15.500 0.9189 0.07404 0.06753 0.0452 0.0198 0.9761
15.750 0.9155 0.07755 0.07116 0.0444 0.0189 1.0000
16.000 0.9132 0.08168 0.07554 0.0433 0.0181 1.0000
16.250 0.9082 0.08637 0.08052 0.0414 0.0173 1.0000
16.500 0.9011 0.09147 0.08588 0.0392 0.0168 1.0000
16.750 0.8921 0.09706 0.09171 0.0365 0.0163 1.0000
17.000 0.8801 0.10338 0.09827 0.0330 0.0157 1.0000
17.250 0.8679 0.11002 0.10513 0.0292 0.0156 1.0000
17.500 0.8518 0.11782 0.11314 0.0247 0.0157 1.0000
17.750 0.8336 0.12646 0.12199 0.0194 0.0158 1.0000
18.000 0.8117 0.13656 0.13222 0.0131 0.0164 1.0000
18.250 0.7849 0.14882 0.14463 0.0058 0.0169 1.0000
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