EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 100,000 Max Cl/Cd: 43.93 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e343-il-100000-n5.txt Download as CSV file: xf-e343-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2976 0.09708 0.09262 -0.0340 1.0000 0.0480
-9.000 -0.2987 0.09362 0.08924 -0.0355 1.0000 0.0481
-8.750 -0.3037 0.08982 0.08553 -0.0376 1.0000 0.0489
-8.500 -0.3133 0.08570 0.08153 -0.0405 1.0000 0.0494
-8.250 -0.3273 0.07977 0.07549 -0.0495 0.9214 0.0507
-8.000 -0.2945 0.07407 0.06965 -0.0553 0.8730 0.0496
-7.750 -0.3087 0.06404 0.05913 -0.0577 0.8400 0.0254
-7.500 -0.2998 0.06119 0.05608 -0.0578 0.8065 0.0249
-7.250 -0.2970 0.05828 0.05294 -0.0566 0.7799 0.0243
-7.000 -0.2939 0.05538 0.04979 -0.0551 0.7585 0.0236
-6.750 -0.2917 0.05207 0.04619 -0.0530 0.7408 0.0231
-6.500 -0.2862 0.04913 0.04294 -0.0509 0.7245 0.0231
-6.250 -0.2788 0.04633 0.03982 -0.0487 0.7097 0.0236
-6.000 -0.2691 0.04354 0.03669 -0.0465 0.6963 0.0236
-5.750 -0.2574 0.04091 0.03367 -0.0442 0.6833 0.0241
-5.500 -0.2447 0.03819 0.03052 -0.0418 0.6711 0.0247
-5.250 -0.2292 0.03582 0.02774 -0.0396 0.6598 0.0246
-5.000 -0.2120 0.03355 0.02505 -0.0376 0.6484 0.0244
-4.750 -0.1924 0.03149 0.02258 -0.0358 0.6376 0.0243
-4.500 -0.1708 0.02949 0.02011 -0.0342 0.6277 0.0243
-4.250 -0.1468 0.02771 0.01795 -0.0330 0.6170 0.0246
-4.000 -0.1206 0.02615 0.01598 -0.0321 0.6080 0.0250
-3.750 -0.0928 0.02469 0.01423 -0.0316 0.5978 0.0256
-3.500 -0.0662 0.02367 0.01308 -0.0312 0.5890 0.0265
-3.250 -0.0399 0.02290 0.01221 -0.0307 0.5793 0.0284
-3.000 -0.0136 0.02210 0.01125 -0.0302 0.5714 0.0315
-2.750 0.0115 0.02138 0.01050 -0.0295 0.5628 0.0341
-2.500 0.0350 0.02066 0.00966 -0.0284 0.5562 0.0369
-2.250 0.0579 0.02019 0.00913 -0.0273 0.5483 0.0426
-2.000 0.0804 0.01971 0.00859 -0.0261 0.5413 0.0503
-1.750 0.1035 0.01923 0.00811 -0.0250 0.5347 0.0654
-1.500 0.1757 0.01739 0.00931 -0.0309 0.5255 0.8483
-1.250 0.2805 0.01927 0.01063 -0.0421 0.5160 0.9438
-1.000 0.3491 0.01934 0.01036 -0.0497 0.5075 0.9695
-0.750 0.3827 0.01922 0.00998 -0.0511 0.5020 0.9736
-0.500 0.4125 0.01916 0.00979 -0.0519 0.4954 0.9778
-0.250 0.4444 0.01906 0.00952 -0.0530 0.4898 0.9812
0.000 0.4736 0.01905 0.00932 -0.0535 0.4855 0.9849
0.250 0.5049 0.01899 0.00918 -0.0546 0.4799 0.9879
0.500 0.5351 0.01896 0.00905 -0.0554 0.4746 0.9909
0.750 0.5644 0.01898 0.00892 -0.0561 0.4701 0.9939
1.000 0.5945 0.01898 0.00882 -0.0569 0.4655 0.9964
1.250 0.6241 0.01901 0.00882 -0.0577 0.4606 0.9990
1.500 0.6495 0.01912 0.00886 -0.0575 0.4565 1.0000
1.750 0.6719 0.01926 0.00890 -0.0567 0.4529 1.0000
2.000 0.6941 0.01943 0.00901 -0.0559 0.4492 1.0000
2.250 0.7157 0.01963 0.00923 -0.0551 0.4448 1.0000
2.500 0.7377 0.01982 0.00940 -0.0543 0.4407 1.0000
2.750 0.7599 0.02000 0.00954 -0.0534 0.4373 1.0000
3.000 0.7824 0.02020 0.00967 -0.0527 0.4344 1.0000
3.250 0.8036 0.02046 0.00997 -0.0518 0.4306 1.0000
3.500 0.8245 0.02072 0.01028 -0.0508 0.4264 1.0000
3.750 0.8460 0.02096 0.01052 -0.0499 0.4228 1.0000
4.000 0.8679 0.02119 0.01074 -0.0490 0.4198 1.0000
4.250 0.8903 0.02141 0.01090 -0.0482 0.4170 1.0000
4.500 0.9097 0.02177 0.01137 -0.0470 0.4131 1.0000
4.750 0.9294 0.02211 0.01179 -0.0459 0.4092 1.0000
5.000 0.9498 0.02241 0.01212 -0.0448 0.4058 1.0000
5.250 0.9710 0.02267 0.01240 -0.0439 0.4028 1.0000
5.500 0.9931 0.02293 0.01262 -0.0430 0.4002 1.0000
5.750 1.0098 0.02341 0.01326 -0.0415 0.3962 1.0000
6.000 1.0273 0.02385 0.01383 -0.0400 0.3924 1.0000
6.250 1.0462 0.02421 0.01425 -0.0387 0.3889 1.0000
6.500 1.0664 0.02450 0.01455 -0.0376 0.3860 1.0000
6.750 1.0881 0.02477 0.01479 -0.0367 0.3834 1.0000
7.000 1.1004 0.02542 0.01567 -0.0345 0.3792 1.0000
7.250 1.1150 0.02594 0.01634 -0.0326 0.3754 1.0000
7.500 1.1319 0.02632 0.01678 -0.0310 0.3718 1.0000
7.750 1.1516 0.02658 0.01707 -0.0298 0.3688 1.0000
8.000 1.1685 0.02700 0.01755 -0.0282 0.3656 1.0000
8.250 1.1756 0.02775 0.01852 -0.0253 0.3611 1.0000
8.500 1.1873 0.02825 0.01915 -0.0230 0.3571 1.0000
8.750 1.2037 0.02855 0.01950 -0.0212 0.3537 1.0000
9.000 1.2251 0.02869 0.01962 -0.0202 0.3507 1.0000
9.250 1.2227 0.02964 0.02083 -0.0159 0.3461 1.0000
9.500 1.2265 0.03027 0.02161 -0.0124 0.3418 1.0000
9.750 1.2382 0.03058 0.02200 -0.0100 0.3381 1.0000
10.000 1.2587 0.03064 0.02204 -0.0088 0.3349 1.0000
10.250 1.2453 0.03169 0.02332 -0.0030 0.3304 1.0000
10.500 1.2374 0.03250 0.02426 0.0021 0.3261 1.0000
10.750 1.2432 0.03282 0.02464 0.0053 0.3223 1.0000
11.000 1.2664 0.03267 0.02448 0.0062 0.3187 1.0000
11.250 1.2259 0.03433 0.02632 0.0151 0.3146 1.0000
11.500 1.2083 0.03585 0.02796 0.0198 0.3099 1.0000
11.750 1.2228 0.03608 0.02823 0.0212 0.3056 1.0000
12.000 1.2187 0.03743 0.02968 0.0237 0.3011 1.0000
12.250 1.1692 0.04236 0.03479 0.0268 0.2948 1.0000
12.500 1.1913 0.04217 0.03465 0.0275 0.2902 1.0000
12.750 1.0773 0.05576 0.04837 0.0268 0.2785 1.0000
13.000 1.1170 0.05343 0.04612 0.0280 0.2758 1.0000
13.500 1.0349 0.06854 0.06132 0.0251 0.2563 1.0000
14.000 1.0263 0.07499 0.06790 0.0240 0.2425 1.0000
14.500 1.0402 0.07845 0.07151 0.0237 0.2311 1.0000
15.000 0.9945 0.09119 0.08436 0.0200 0.2123 1.0000
15.250 0.9953 0.09411 0.08736 0.0192 0.2057 1.0000
15.500 1.0288 0.09178 0.08512 0.0203 0.2034 1.0000
16.000 1.0253 0.09850 0.09198 0.0183 0.1901 1.0000
16.500 1.0249 0.10490 0.09852 0.0162 0.1769 1.0000
17.000 1.0232 0.11173 0.10550 0.0137 0.1640 1.0000
17.250 1.0637 0.10797 0.10177 0.0154 0.1611 1.0000
17.500 1.0217 0.11868 0.11258 0.0110 0.1517 1.0000
17.750 1.0584 0.11543 0.10936 0.0125 0.1484 1.0000
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Polar data table (+)
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