E226 (10.19%) (e226-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 100,000 Max Cl/Cd: 44.24 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e226-il-100000-n5.txt Download as CSV file: xf-e226-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5021 0.09147 0.08669 -0.0181 1.0000 0.0255
-10.750 -0.6711 0.07344 0.06821 -0.0319 1.0000 0.0217
-10.500 -0.6836 0.06754 0.06227 -0.0363 1.0000 0.0215
-10.250 -0.7026 0.06184 0.05644 -0.0406 1.0000 0.0214
-10.000 -0.7186 0.05768 0.05216 -0.0421 1.0000 0.0212
-9.750 -0.7345 0.05420 0.04850 -0.0414 1.0000 0.0211
-9.500 -0.7474 0.05042 0.04440 -0.0404 1.0000 0.0213
-9.250 -0.7515 0.04699 0.04064 -0.0392 1.0000 0.0213
-9.000 -0.7526 0.04364 0.03682 -0.0377 1.0000 0.0216
-8.750 -0.7472 0.04059 0.03347 -0.0364 1.0000 0.0220
-8.500 -0.7376 0.03786 0.03045 -0.0350 1.0000 0.0222
-8.250 -0.7253 0.03538 0.02766 -0.0336 1.0000 0.0224
-8.000 -0.7108 0.03315 0.02515 -0.0322 1.0000 0.0226
-7.750 -0.6948 0.03114 0.02290 -0.0309 1.0000 0.0230
-7.500 -0.6776 0.02935 0.02091 -0.0295 1.0000 0.0234
-7.250 -0.6599 0.02771 0.01909 -0.0281 1.0000 0.0240
-7.000 -0.6419 0.02623 0.01746 -0.0266 1.0000 0.0247
-6.750 -0.6241 0.02491 0.01599 -0.0250 1.0000 0.0254
-6.500 -0.6064 0.02375 0.01469 -0.0234 1.0000 0.0267
-6.250 -0.5894 0.02265 0.01350 -0.0217 1.0000 0.0286
-6.000 -0.5723 0.02171 0.01253 -0.0202 1.0000 0.0307
-5.750 -0.5549 0.02081 0.01153 -0.0185 1.0000 0.0330
-5.250 -0.5204 0.01903 0.00956 -0.0151 1.0000 0.0401
-5.000 -0.5030 0.01809 0.00863 -0.0134 1.0000 0.0521
-4.750 -0.4859 0.01712 0.00790 -0.0118 1.0000 0.0882
-4.500 -0.4683 0.01633 0.00741 -0.0105 1.0000 0.1441
-4.000 -0.4297 0.01505 0.00679 -0.0086 0.9987 0.2835
-3.750 -0.3951 0.01458 0.00655 -0.0105 0.9912 0.3520
-3.500 -0.3593 0.01424 0.00635 -0.0124 0.9843 0.4085
-3.250 -0.3255 0.01394 0.00614 -0.0138 0.9760 0.4609
-3.000 -0.2910 0.01368 0.00600 -0.0152 0.9682 0.5118
-2.750 -0.2559 0.01346 0.00589 -0.0166 0.9604 0.5617
-2.500 -0.2221 0.01328 0.00578 -0.0177 0.9520 0.6084
-2.250 -0.1855 0.01312 0.00570 -0.0191 0.9448 0.6535
-2.000 -0.1535 0.01298 0.00563 -0.0196 0.9351 0.6947
-1.750 -0.1177 0.01288 0.00557 -0.0207 0.9274 0.7346
-1.500 -0.0864 0.01280 0.00554 -0.0208 0.9169 0.7707
-1.250 -0.0542 0.01274 0.00549 -0.0211 0.9066 0.8046
-1.000 -0.0185 0.01269 0.00544 -0.0220 0.8976 0.8355
-0.750 0.0154 0.01267 0.00541 -0.0226 0.8861 0.8635
-0.500 0.0518 0.01265 0.00537 -0.0237 0.8744 0.8884
-0.250 0.0901 0.01262 0.00530 -0.0253 0.8627 0.9105
0.000 0.1302 0.01259 0.00522 -0.0273 0.8502 0.9295
0.250 0.1713 0.01255 0.00514 -0.0296 0.8367 0.9461
0.500 0.2125 0.01250 0.00505 -0.0320 0.8216 0.9611
0.750 0.2542 0.01245 0.00496 -0.0346 0.8050 0.9749
1.000 0.2959 0.01238 0.00486 -0.0373 0.7870 0.9878
1.250 0.3368 0.01231 0.00475 -0.0400 0.7680 1.0000
1.500 0.3580 0.01232 0.00471 -0.0386 0.7490 1.0000
1.750 0.3791 0.01236 0.00470 -0.0372 0.7290 1.0000
2.000 0.4005 0.01243 0.00472 -0.0359 0.7085 1.0000
2.500 0.4442 0.01262 0.00482 -0.0332 0.6659 1.0000
2.750 0.4663 0.01274 0.00488 -0.0320 0.6439 1.0000
3.000 0.4884 0.01289 0.00500 -0.0307 0.6201 1.0000
3.250 0.5107 0.01307 0.00513 -0.0295 0.5963 1.0000
3.500 0.5329 0.01327 0.00528 -0.0282 0.5711 1.0000
3.750 0.5551 0.01349 0.00546 -0.0270 0.5445 1.0000
4.000 0.5772 0.01374 0.00566 -0.0258 0.5170 1.0000
4.250 0.5993 0.01402 0.00590 -0.0245 0.4883 1.0000
4.500 0.6212 0.01433 0.00616 -0.0233 0.4582 1.0000
4.750 0.6431 0.01468 0.00645 -0.0222 0.4271 1.0000
5.000 0.6647 0.01507 0.00677 -0.0210 0.3950 1.0000
5.250 0.6861 0.01551 0.00715 -0.0198 0.3619 1.0000
5.500 0.7074 0.01599 0.00757 -0.0187 0.3273 1.0000
5.750 0.7282 0.01653 0.00802 -0.0176 0.2915 1.0000
6.000 0.7487 0.01713 0.00853 -0.0165 0.2560 1.0000
6.250 0.7692 0.01777 0.00913 -0.0154 0.2217 1.0000
6.500 0.7887 0.01853 0.00976 -0.0142 0.1861 1.0000
6.750 0.8073 0.01941 0.01044 -0.0131 0.1453 1.0000
7.000 0.8255 0.02040 0.01119 -0.0120 0.1053 1.0000
7.250 0.8437 0.02141 0.01210 -0.0109 0.0754 1.0000
7.500 0.8607 0.02260 0.01318 -0.0096 0.0522 1.0000
7.750 0.8766 0.02391 0.01446 -0.0080 0.0383 1.0000
8.000 0.8915 0.02529 0.01589 -0.0064 0.0325 1.0000
8.250 0.9067 0.02657 0.01730 -0.0047 0.0292 1.0000
8.500 0.9200 0.02799 0.01880 -0.0031 0.0273 1.0000
8.750 0.9336 0.02944 0.02041 -0.0013 0.0258 1.0000
9.000 0.9476 0.03087 0.02202 0.0003 0.0241 1.0000
9.250 0.9610 0.03227 0.02353 0.0018 0.0226 1.0000
9.500 0.9722 0.03380 0.02512 0.0033 0.0214 1.0000
9.750 0.9836 0.03558 0.02704 0.0049 0.0206 1.0000
10.000 0.9951 0.03752 0.02921 0.0066 0.0200 1.0000
10.250 1.0046 0.03956 0.03147 0.0083 0.0196 1.0000
10.500 1.0114 0.04178 0.03396 0.0101 0.0193 1.0000
10.750 1.0150 0.04423 0.03667 0.0120 0.0189 1.0000
11.000 1.0157 0.04683 0.03952 0.0137 0.0187 1.0000
11.250 1.0129 0.04969 0.04265 0.0152 0.0186 1.0000
11.500 1.0064 0.05290 0.04612 0.0162 0.0184 1.0000
11.750 0.9972 0.05647 0.04995 0.0165 0.0183 1.0000
12.000 0.9847 0.06063 0.05438 0.0160 0.0183 1.0000
12.250 0.9696 0.06544 0.05943 0.0144 0.0184 1.0000
12.500 0.9515 0.07113 0.06535 0.0116 0.0184 1.0000
12.750 0.9304 0.07797 0.07241 0.0075 0.0185 1.0000
13.000 0.9072 0.08604 0.08069 0.0021 0.0187 1.0000
13.250 0.8805 0.09590 0.09072 -0.0047 0.0191 1.0000
13.500 0.8506 0.10783 0.10275 -0.0127 0.0195 1.0000
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Polar data table (+)
Polar graphs
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