EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 100,000 Max Cl/Cd: 33.56 at α=12° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e550-il-100000.txt Download as CSV file: xf-e550-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4043 0.11463 0.10995 -0.0435 1.0000 0.1423
-11.500 -0.4904 0.08336 0.07859 -0.0620 1.0000 0.0678
-11.250 -0.5503 0.07482 0.06988 -0.0665 1.0000 0.0655
-11.000 -0.5772 0.06961 0.06450 -0.0671 1.0000 0.0602
-10.750 -0.6002 0.06547 0.06029 -0.0665 1.0000 0.0583
-10.500 -0.6384 0.06174 0.05638 -0.0641 1.0000 0.0563
-10.250 -0.7109 0.06049 0.05465 -0.0559 1.0000 0.0538
-10.000 -0.6970 0.05677 0.05099 -0.0549 1.0000 0.0519
-9.750 -0.7078 0.05452 0.04872 -0.0514 1.0000 0.0510
-9.500 -0.7374 0.05426 0.04851 -0.0447 1.0000 0.0508
-9.250 -0.7267 0.04976 0.04360 -0.0465 0.9902 0.0487
-9.000 -0.7047 0.04410 0.03682 -0.0495 0.9740 0.0457
-8.750 -0.6664 0.04018 0.03253 -0.0529 0.9621 0.0460
-8.500 -0.6225 0.03758 0.02991 -0.0569 0.9515 0.0494
-8.250 -0.5753 0.03464 0.02654 -0.0607 0.9432 0.0521
-8.000 -0.5243 0.03161 0.02336 -0.0639 0.9340 0.0550
-7.750 -0.4702 0.02953 0.02116 -0.0681 0.9256 0.0627
-7.500 -0.4189 0.02743 0.01925 -0.0712 0.9141 0.0746
-7.250 -0.3792 0.02565 0.01774 -0.0733 0.8991 0.0957
-7.000 -0.3581 0.02398 0.01637 -0.0732 0.8810 0.1319
-6.750 -0.3589 0.02199 0.01490 -0.0708 0.8619 0.1948
-6.500 -0.3786 0.01953 0.01361 -0.0662 0.8441 0.3527
-6.250 -0.3597 0.02227 0.01687 -0.0610 0.8289 0.5529
-6.000 -0.3230 0.02550 0.01990 -0.0577 0.8155 0.5857
-5.750 -0.2648 0.02971 0.02390 -0.0552 0.8046 0.6045
-5.500 -0.2062 0.03280 0.02669 -0.0540 0.7948 0.6211
-5.250 -0.1659 0.03435 0.02804 -0.0527 0.7835 0.6369
-5.000 -0.1212 0.03559 0.02902 -0.0524 0.7740 0.6532
-4.750 -0.0633 0.03665 0.02983 -0.0540 0.7641 0.6704
-4.500 -0.0326 0.03691 0.02991 -0.0536 0.7552 0.6862
-4.250 0.0146 0.03700 0.02979 -0.0555 0.7471 0.6985
-4.000 0.0520 0.03683 0.02946 -0.0565 0.7396 0.7097
-3.750 0.0573 0.03644 0.02900 -0.0539 0.7321 0.7201
-3.500 0.0954 0.03619 0.02856 -0.0552 0.7260 0.7297
-3.250 0.1070 0.03579 0.02813 -0.0535 0.7184 0.7376
-3.000 0.1366 0.03544 0.02764 -0.0540 0.7126 0.7450
-2.750 0.1312 0.03507 0.02724 -0.0502 0.7075 0.7494
-2.500 0.1634 0.03468 0.02679 -0.0513 0.7012 0.7554
-2.250 0.1846 0.03430 0.02632 -0.0509 0.6962 0.7599
-2.000 0.1895 0.03398 0.02594 -0.0484 0.6916 0.7627
-1.750 0.1767 0.03377 0.02578 -0.0433 0.6860 0.7650
-1.500 0.1669 0.03339 0.02539 -0.0388 0.6814 0.7676
-1.250 0.2049 0.03307 0.02494 -0.0405 0.6777 0.7706
-1.000 0.2146 0.03297 0.02487 -0.0387 0.6730 0.7727
-0.750 0.2212 0.03284 0.02476 -0.0365 0.6681 0.7751
-0.500 0.2297 0.03255 0.02443 -0.0345 0.6639 0.7771
-0.250 0.2405 0.03222 0.02402 -0.0330 0.6606 0.7796
0.000 0.2351 0.03227 0.02413 -0.0297 0.6557 0.7818
0.250 0.2397 0.03227 0.02416 -0.0279 0.6512 0.7840
0.500 0.2622 0.03220 0.02406 -0.0275 0.6474 0.7861
0.750 0.2881 0.03200 0.02378 -0.0278 0.6444 0.7880
1.000 0.2916 0.03247 0.02433 -0.0257 0.6392 0.7899
1.250 0.2982 0.03295 0.02487 -0.0240 0.6345 0.7927
1.500 0.3181 0.03301 0.02491 -0.0240 0.6308 0.7954
1.750 0.3477 0.03281 0.02463 -0.0253 0.6280 0.7974
2.000 0.3471 0.03393 0.02584 -0.0239 0.6221 0.7998
2.250 0.3502 0.03491 0.02691 -0.0217 0.6168 0.8023
2.500 0.3759 0.03499 0.02697 -0.0218 0.6134 0.8048
2.750 0.4114 0.03475 0.02670 -0.0231 0.6110 0.8072
3.000 0.3635 0.03850 0.03062 -0.0179 0.6009 0.8105
3.250 0.3957 0.03854 0.03066 -0.0193 0.5974 0.8130
3.500 0.4396 0.03812 0.03019 -0.0218 0.5952 0.8158
3.750 0.3501 0.04407 0.03630 -0.0135 0.5826 0.8198
4.000 0.3907 0.04359 0.03583 -0.0146 0.5798 0.8227
4.250 0.4488 0.04246 0.03471 -0.0173 0.5783 0.8254
4.500 0.3753 0.04867 0.04096 -0.0129 0.5658 0.8299
4.750 0.4206 0.04812 0.04044 -0.0145 0.5627 0.8328
5.000 0.4768 0.04661 0.03896 -0.0158 0.5610 0.8356
5.250 0.4139 0.05238 0.04479 -0.0123 0.5486 0.8406
5.500 0.4662 0.05135 0.04379 -0.0138 0.5455 0.8449
5.750 0.4326 0.05547 0.04795 -0.0121 0.5348 0.8496
6.000 0.4713 0.05503 0.04757 -0.0124 0.5305 0.8538
6.250 0.4618 0.05778 0.05037 -0.0117 0.5212 0.8588
6.500 0.4919 0.05814 0.05077 -0.0125 0.5154 0.8639
6.750 0.5445 0.05668 0.04940 -0.0129 0.5125 0.8690
7.000 0.5167 0.06062 0.05339 -0.0117 0.4999 0.8756
7.250 0.5658 0.05940 0.05226 -0.0122 0.4967 0.8826
7.500 0.5451 0.06287 0.05579 -0.0111 0.4843 0.8907
7.750 0.5923 0.06155 0.05458 -0.0113 0.4808 0.8998
8.000 0.5771 0.06483 0.05794 -0.0107 0.4683 0.9106
8.250 0.6252 0.06326 0.05651 -0.0107 0.4649 0.9239
8.500 0.6183 0.06655 0.05993 -0.0116 0.4520 0.9427
11.000 1.0945 0.04701 0.04147 -0.0198 0.4003 1.0000
11.250 1.0547 0.05278 0.04723 -0.0188 0.3846 1.0000
11.500 1.0265 0.05809 0.05254 -0.0186 0.3685 1.0000
11.750 1.1266 0.04850 0.04318 -0.0173 0.3667 1.0000
12.000 1.2591 0.03752 0.03226 -0.0185 0.3541 1.0000
12.250 1.2630 0.03828 0.03303 -0.0169 0.3388 1.0000
12.500 1.2628 0.03961 0.03436 -0.0155 0.3225 1.0000
12.750 1.2616 0.04126 0.03597 -0.0142 0.3051 1.0000
13.000 1.2623 0.04290 0.03754 -0.0131 0.2869 1.0000
13.250 1.2646 0.04452 0.03905 -0.0121 0.2685 1.0000
13.500 1.2696 0.04601 0.04032 -0.0112 0.2497 1.0000
13.750 1.2632 0.04876 0.04301 -0.0105 0.2333 1.0000
14.000 1.2576 0.05156 0.04573 -0.0100 0.2176 1.0000
14.250 1.2530 0.05437 0.04846 -0.0096 0.2026 1.0000
14.500 1.2493 0.05720 0.05120 -0.0093 0.1882 1.0000
14.750 1.2470 0.05998 0.05388 -0.0092 0.1746 1.0000
15.000 1.2461 0.06268 0.05647 -0.0091 0.1615 1.0000
15.250 1.2370 0.06656 0.06047 -0.0096 0.1510 1.0000
15.500 1.2340 0.06981 0.06372 -0.0099 0.1401 1.0000
15.750 1.2344 0.07269 0.06653 -0.0101 0.1299 1.0000
16.000 1.2402 0.07492 0.06860 -0.0100 0.1194 1.0000
16.250 1.2311 0.07928 0.07317 -0.0111 0.1124 1.0000
16.500 1.2344 0.08200 0.07583 -0.0114 0.1042 1.0000
16.750 1.2320 0.08553 0.07943 -0.0122 0.0975 1.0000
17.000 1.2328 0.08879 0.08273 -0.0128 0.0911 1.0000
17.250 1.2316 0.09228 0.08627 -0.0138 0.0853 1.0000
17.500 1.2337 0.09546 0.08949 -0.0144 0.0800 1.0000
17.750 1.2254 0.10014 0.09436 -0.0161 0.0761 1.0000
18.000 1.2381 0.10178 0.09586 -0.0160 0.0704 1.0000
18.250 1.2234 0.10761 0.10200 -0.0185 0.0681 1.0000
18.500 1.2125 0.11295 0.10755 -0.0208 0.0654 1.0000
18.750 1.2297 0.11386 0.10826 -0.0204 0.0605 1.0000
19.000 1.2092 0.12086 0.11559 -0.0240 0.0595 1.0000
19.250 1.1876 0.12837 0.12338 -0.0280 0.0586 1.0000
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Polar data table (+)
Polar graphs
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