EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 50,000 Max Cl/Cd: 11.14 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e550-il-50000-n5.txt Download as CSV file: xf-e550-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4821 0.10071 0.09344 -0.0549 1.0000 0.0380
-12.750 -0.4981 0.09422 0.08692 -0.0582 1.0000 0.0377
-12.500 -0.5157 0.08822 0.08087 -0.0612 1.0000 0.0374
-12.250 -0.5379 0.08227 0.07482 -0.0639 1.0000 0.0372
-12.000 -0.5572 0.07722 0.06966 -0.0657 1.0000 0.0370
-11.750 -0.5758 0.07270 0.06500 -0.0667 1.0000 0.0369
-11.500 -0.5934 0.06859 0.06074 -0.0671 1.0000 0.0368
-11.250 -0.6090 0.06498 0.05695 -0.0668 1.0000 0.0369
-11.000 -0.6220 0.06181 0.05360 -0.0658 1.0000 0.0370
-10.750 -0.6333 0.05888 0.05047 -0.0644 1.0000 0.0372
-10.500 -0.6456 0.05623 0.04758 -0.0622 1.0000 0.0377
-10.250 -0.6510 0.05400 0.04524 -0.0599 1.0000 0.0385
-10.000 -0.6501 0.05233 0.04359 -0.0578 1.0000 0.0396
-9.750 -0.6500 0.05068 0.04189 -0.0554 1.0000 0.0407
-9.500 -0.6486 0.04895 0.04004 -0.0528 1.0000 0.0420
-9.250 -0.6445 0.04724 0.03815 -0.0502 1.0000 0.0434
-9.000 -0.6381 0.04579 0.03649 -0.0475 1.0000 0.0447
-8.750 -0.6059 0.04403 0.03475 -0.0481 0.9957 0.0477
-8.500 -0.5477 0.04230 0.03283 -0.0507 0.9881 0.0547
-8.250 -0.4988 0.04110 0.03153 -0.0524 0.9723 0.0637
-8.000 -0.4612 0.03979 0.03023 -0.0541 0.9528 0.0748
-7.750 -0.4290 0.03810 0.02866 -0.0563 0.9339 0.0905
-7.500 -0.4004 0.03615 0.02682 -0.0589 0.9154 0.1149
-7.250 -0.3821 0.03380 0.02479 -0.0609 0.8959 0.1504
-7.000 -0.3776 0.03132 0.02274 -0.0613 0.8748 0.2051
-6.750 -0.3802 0.02941 0.02180 -0.0591 0.8551 0.3110
-6.500 -0.3353 0.03308 0.02591 -0.0553 0.8413 0.4906
-6.250 -0.3209 0.03371 0.02620 -0.0532 0.8251 0.5321
-6.000 -0.2936 0.03525 0.02739 -0.0510 0.8115 0.5625
-5.750 -0.2754 0.03605 0.02791 -0.0485 0.7978 0.5864
-5.500 -0.2338 0.03784 0.02936 -0.0470 0.7865 0.6059
-5.250 -0.1986 0.03871 0.02991 -0.0460 0.7765 0.6230
-5.000 -0.1788 0.03885 0.02983 -0.0444 0.7652 0.6373
-4.750 -0.1501 0.03893 0.02963 -0.0438 0.7558 0.6474
-4.500 -0.1283 0.03868 0.02916 -0.0430 0.7466 0.6561
-4.250 -0.1104 0.03839 0.02868 -0.0419 0.7375 0.6646
-4.000 -0.0918 0.03799 0.02808 -0.0409 0.7295 0.6717
-3.750 -0.0693 0.03776 0.02767 -0.0403 0.7215 0.6776
-3.500 -0.0632 0.03719 0.02697 -0.0384 0.7141 0.6859
-3.250 -0.0345 0.03698 0.02656 -0.0385 0.7077 0.6897
-3.000 -0.0167 0.03672 0.02619 -0.0376 0.7002 0.6950
-2.750 -0.0080 0.03613 0.02544 -0.0361 0.6945 0.7020
-2.500 0.0151 0.03602 0.02524 -0.0357 0.6875 0.7052
-2.250 0.0362 0.03579 0.02488 -0.0351 0.6815 0.7091
-2.000 0.0553 0.03541 0.02435 -0.0346 0.6770 0.7138
-1.750 0.0615 0.03518 0.02408 -0.0327 0.6703 0.7189
-1.500 0.0841 0.03505 0.02386 -0.0323 0.6649 0.7218
-1.250 0.1085 0.03482 0.02349 -0.0322 0.6607 0.7250
-1.000 0.1199 0.03481 0.02346 -0.0307 0.6545 0.7290
-0.750 0.1325 0.03462 0.02320 -0.0297 0.6493 0.7333
-0.500 0.1552 0.03447 0.02295 -0.0295 0.6453 0.7363
-0.250 0.1744 0.03453 0.02297 -0.0287 0.6407 0.7391
0.000 0.1878 0.03469 0.02313 -0.0274 0.6349 0.7423
0.250 0.2078 0.03464 0.02301 -0.0270 0.6306 0.7455
0.500 0.2313 0.03448 0.02275 -0.0273 0.6273 0.7494
0.750 0.2403 0.03492 0.02323 -0.0256 0.6216 0.7527
1.000 0.2568 0.03520 0.02352 -0.0247 0.6167 0.7554
1.250 0.2803 0.03525 0.02353 -0.0247 0.6130 0.7581
1.500 0.3077 0.03521 0.02341 -0.0251 0.6101 0.7612
1.750 0.3077 0.03612 0.02441 -0.0230 0.6031 0.7657
2.000 0.3265 0.03645 0.02475 -0.0226 0.5988 0.7689
2.250 0.3520 0.03657 0.02486 -0.0226 0.5955 0.7717
2.500 0.3632 0.03727 0.02560 -0.0214 0.5904 0.7750
2.750 0.3695 0.03822 0.02660 -0.0200 0.5843 0.7788
3.000 0.3936 0.03853 0.02691 -0.0205 0.5806 0.7827
3.250 0.4226 0.03861 0.02698 -0.0209 0.5779 0.7859
3.500 0.4086 0.04053 0.02903 -0.0176 0.5693 0.7902
3.750 0.4281 0.04111 0.02963 -0.0174 0.5650 0.7942
4.000 0.4593 0.04123 0.02977 -0.0184 0.5622 0.7980
4.500 0.4594 0.04417 0.03286 -0.0148 0.5485 0.8064
4.750 0.4911 0.04429 0.03301 -0.0155 0.5457 0.8109
5.250 0.4913 0.04773 0.03661 -0.0128 0.5311 0.8214
5.500 0.5247 0.04759 0.03653 -0.0132 0.5287 0.8264
6.000 0.5316 0.05125 0.04035 -0.0119 0.5135 0.8380
6.500 0.5447 0.05456 0.04385 -0.0109 0.4988 0.8519
6.750 0.5771 0.05437 0.04377 -0.0109 0.4960 0.8595
7.250 0.5917 0.05754 0.04718 -0.0100 0.4807 0.8785
7.500 0.5822 0.06036 0.05012 -0.0093 0.4698 0.8901
7.750 0.6111 0.06050 0.05041 -0.0095 0.4655 0.9038
8.250 0.6440 0.06327 0.05351 -0.0115 0.4497 0.9709
8.500 0.6454 0.06593 0.05624 -0.0126 0.4389 1.0000
8.750 0.6768 0.06628 0.05668 -0.0137 0.4338 1.0000
9.000 0.6778 0.06908 0.05952 -0.0146 0.4227 1.0000
9.250 0.7098 0.06919 0.05973 -0.0153 0.4177 1.0000
9.750 0.7425 0.07190 0.06259 -0.0164 0.4015 1.0000
10.000 0.7385 0.07512 0.06587 -0.0171 0.3892 1.0000
10.250 0.7748 0.07438 0.06525 -0.0171 0.3852 1.0000
10.500 0.7697 0.07772 0.06865 -0.0177 0.3726 1.0000
10.750 0.7702 0.08056 0.07156 -0.0182 0.3611 1.0000
11.000 0.8020 0.07999 0.07111 -0.0180 0.3561 1.0000
11.250 0.7990 0.08323 0.07442 -0.0186 0.3437 1.0000
11.750 0.8303 0.08537 0.07680 -0.0186 0.3268 1.0000
12.000 0.8285 0.08865 0.08015 -0.0193 0.3148 1.0000
12.250 0.8565 0.08799 0.07962 -0.0187 0.3089 1.0000
12.500 0.8590 0.09069 0.08243 -0.0193 0.2975 1.0000
13.000 0.8930 0.09190 0.08389 -0.0188 0.2809 1.0000
13.250 0.8871 0.09605 0.08812 -0.0199 0.2684 1.0000
13.750 0.9220 0.09681 0.08916 -0.0193 0.2516 1.0000
14.000 0.9155 0.10132 0.09374 -0.0207 0.2396 1.0000
14.250 0.9625 0.09648 0.08906 -0.0182 0.2345 1.0000
14.750 0.9451 0.10640 0.09913 -0.0215 0.2108 1.0000
15.000 0.9843 0.10267 0.09553 -0.0194 0.2035 1.0000
15.250 0.9847 0.10602 0.09897 -0.0205 0.1928 1.0000
15.500 0.9706 0.11229 0.10531 -0.0229 0.1823 1.0000
15.750 1.0031 0.10961 0.10268 -0.0212 0.1735 1.0000
16.000 1.0041 0.11300 0.10614 -0.0224 0.1640 1.0000
16.250 0.9846 0.12058 0.11381 -0.0258 0.1552 1.0000
16.500 1.0230 0.11652 0.10974 -0.0234 0.1461 1.0000
16.750 0.9833 0.12850 0.12187 -0.0291 0.1388 1.0000
17.000 1.0049 0.12774 0.12113 -0.0284 0.1310 1.0000
17.250 0.9729 0.13874 0.13222 -0.0340 0.1242 1.0000
17.500 0.9900 0.13887 0.13238 -0.0339 0.1176 1.0000
17.750 0.9467 0.15352 0.14705 -0.0417 0.1113 1.0000
18.000 0.9841 0.14844 0.14205 -0.0388 0.1056 1.0000
18.250 0.9243 0.16872 0.16224 -0.0500 0.0998 1.0000
18.500 0.9628 0.16249 0.15617 -0.0466 0.0950 1.0000
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Polar data table (+)
Polar graphs
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