E230 (9.96%) (e230-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 50,000 Max Cl/Cd: 24.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e230-il-50000-n5.txt Download as CSV file: xf-e230-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8073 0.09595 0.08925 0.0117 1.0000 0.0353
-11.250 -0.8243 0.08820 0.08143 0.0063 1.0000 0.0350
-11.000 -0.8422 0.08139 0.07454 0.0017 1.0000 0.0347
-10.750 -0.8619 0.07535 0.06836 -0.0018 1.0000 0.0345
-10.500 -0.8800 0.07039 0.06321 -0.0035 1.0000 0.0344
-10.250 -0.8973 0.06602 0.05863 -0.0036 1.0000 0.0343
-10.000 -0.9111 0.06219 0.05455 -0.0023 1.0000 0.0343
-9.750 -0.9201 0.05843 0.05046 -0.0008 1.0000 0.0344
-9.500 -0.9228 0.05472 0.04636 0.0007 1.0000 0.0345
-9.250 -0.9205 0.05108 0.04228 0.0023 1.0000 0.0349
-9.000 -0.9128 0.04776 0.03847 0.0038 1.0000 0.0355
-8.750 -0.9010 0.04485 0.03544 0.0048 1.0000 0.0370
-8.500 -0.8871 0.04250 0.03290 0.0059 1.0000 0.0391
-8.250 -0.8705 0.04010 0.03016 0.0070 1.0000 0.0418
-8.000 -0.8505 0.03768 0.02735 0.0080 1.0000 0.0445
-7.750 -0.8307 0.03539 0.02491 0.0091 1.0000 0.0472
-7.500 -0.8125 0.03345 0.02288 0.0103 1.0000 0.0512
-7.250 -0.7941 0.03157 0.02084 0.0116 1.0000 0.0585
-7.000 -0.7773 0.02974 0.01901 0.0129 1.0000 0.0714
-6.750 -0.7609 0.02785 0.01721 0.0143 1.0000 0.0968
-6.500 -0.7451 0.02620 0.01588 0.0153 1.0000 0.1475
-6.250 -0.7288 0.02478 0.01475 0.0166 1.0000 0.1996
-6.000 -0.7104 0.02369 0.01377 0.0179 1.0000 0.2492
-5.750 -0.6917 0.02275 0.01296 0.0192 1.0000 0.2961
-5.500 -0.6720 0.02194 0.01224 0.0205 1.0000 0.3418
-5.250 -0.6517 0.02121 0.01156 0.0219 1.0000 0.3866
-5.000 -0.6309 0.02056 0.01098 0.0233 1.0000 0.4315
-4.750 -0.6095 0.01998 0.01048 0.0247 1.0000 0.4762
-4.500 -0.5875 0.01947 0.01005 0.0261 1.0000 0.5207
-4.250 -0.5647 0.01903 0.00965 0.0274 1.0000 0.5647
-4.000 -0.5409 0.01866 0.00934 0.0288 1.0000 0.6078
-3.750 -0.5163 0.01838 0.00910 0.0300 1.0000 0.6502
-3.500 -0.4892 0.01820 0.00892 0.0310 1.0000 0.6908
-3.250 -0.4595 0.01810 0.00882 0.0315 1.0000 0.7291
-3.000 -0.4276 0.01808 0.00875 0.0316 1.0000 0.7650
-2.750 -0.3943 0.01811 0.00870 0.0313 1.0000 0.7979
-2.500 -0.3571 0.01821 0.00867 0.0302 1.0000 0.8266
-2.250 -0.3166 0.01833 0.00868 0.0284 1.0000 0.8515
-2.000 -0.2775 0.01841 0.00864 0.0266 1.0000 0.8751
-1.750 -0.2321 0.01850 0.00861 0.0235 1.0000 0.8948
-1.500 -0.1903 0.01853 0.00855 0.0208 1.0000 0.9150
-1.250 -0.1465 0.01850 0.00845 0.0174 1.0000 0.9334
-1.000 -0.1013 0.01840 0.00832 0.0135 1.0000 0.9507
-0.750 -0.0570 0.01825 0.00816 0.0096 1.0000 0.9679
-0.500 -0.0118 0.01806 0.00799 0.0052 1.0000 0.9844
-0.250 0.0373 0.01773 0.00771 -0.0001 1.0000 0.9987
0.000 0.0475 0.01776 0.00781 0.0012 0.9988 1.0000
0.250 0.0944 0.01780 0.00788 -0.0037 0.9616 1.0000
0.500 0.1402 0.01779 0.00791 -0.0078 0.9303 1.0000
0.750 0.1744 0.01781 0.00798 -0.0093 0.8971 1.0000
1.000 0.1995 0.01786 0.00804 -0.0088 0.8653 1.0000
1.250 0.2197 0.01792 0.00810 -0.0071 0.8352 1.0000
1.500 0.2382 0.01798 0.00818 -0.0051 0.8062 1.0000
1.750 0.2562 0.01804 0.00825 -0.0028 0.7782 1.0000
2.000 0.2741 0.01812 0.00832 -0.0005 0.7508 1.0000
2.250 0.2923 0.01820 0.00840 0.0018 0.7234 1.0000
2.500 0.3112 0.01830 0.00853 0.0039 0.6948 1.0000
2.750 0.3305 0.01841 0.00866 0.0060 0.6656 1.0000
3.000 0.3501 0.01854 0.00879 0.0080 0.6354 1.0000
3.250 0.3701 0.01870 0.00894 0.0099 0.6042 1.0000
3.500 0.3905 0.01889 0.00916 0.0117 0.5707 1.0000
3.750 0.4111 0.01912 0.00939 0.0134 0.5356 1.0000
4.000 0.4316 0.01939 0.00962 0.0151 0.4996 1.0000
4.250 0.4525 0.01972 0.00995 0.0166 0.4600 1.0000
4.500 0.4731 0.02012 0.01033 0.0181 0.4192 1.0000
4.750 0.4938 0.02060 0.01076 0.0195 0.3767 1.0000
5.000 0.5144 0.02119 0.01128 0.0207 0.3322 1.0000
5.250 0.5346 0.02190 0.01190 0.0218 0.2866 1.0000
5.500 0.5541 0.02275 0.01266 0.0229 0.2413 1.0000
5.750 0.5730 0.02379 0.01360 0.0240 0.1977 1.0000
6.000 0.5908 0.02506 0.01471 0.0250 0.1549 1.0000
6.250 0.6074 0.02643 0.01584 0.0259 0.1119 1.0000
6.500 0.6237 0.02800 0.01730 0.0271 0.0849 1.0000
6.750 0.6398 0.02962 0.01890 0.0285 0.0696 1.0000
7.000 0.6566 0.03130 0.02070 0.0300 0.0610 1.0000
7.250 0.6731 0.03302 0.02248 0.0315 0.0562 1.0000
7.500 0.6910 0.03503 0.02469 0.0331 0.0528 1.0000
7.750 0.7083 0.03710 0.02707 0.0345 0.0494 1.0000
8.000 0.7234 0.03905 0.02920 0.0357 0.0462 1.0000
8.250 0.7370 0.04128 0.03143 0.0369 0.0439 1.0000
8.500 0.7480 0.04415 0.03481 0.0383 0.0426 1.0000
8.750 0.7554 0.04736 0.03845 0.0396 0.0418 1.0000
9.000 0.7581 0.05083 0.04235 0.0409 0.0414 1.0000
9.250 0.7548 0.05459 0.04647 0.0419 0.0410 1.0000
9.500 0.7464 0.05846 0.05063 0.0427 0.0409 1.0000
9.750 0.7321 0.06244 0.05482 0.0431 0.0410 1.0000
10.000 0.7120 0.06661 0.05911 0.0427 0.0412 1.0000
10.250 0.6907 0.07197 0.06453 0.0400 0.0415 1.0000
10.500 0.6702 0.07855 0.07117 0.0355 0.0419 1.0000
10.750 0.6522 0.08600 0.07863 0.0304 0.0424 1.0000
11.000 0.6384 0.09344 0.08605 0.0259 0.0429 1.0000
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Polar data table (+)
Polar graphs
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