EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 551 AIRFOIL (e551-il) Reynolds number: 100,000 Max Cl/Cd: 43.08 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e551-il-100000.txt Download as CSV file: xf-e551-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 551 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4412 0.10234 0.09732 -0.0677 1.0000 0.0569
-12.750 -0.4401 0.09835 0.09338 -0.0680 1.0000 0.0556
-12.500 -0.4740 0.08879 0.08380 -0.0729 1.0000 0.0530
-12.250 -0.5694 0.07562 0.07030 -0.0817 1.0000 0.0499
-12.000 -0.6269 0.07177 0.06621 -0.0831 1.0000 0.0491
-11.750 -0.6219 0.06789 0.06234 -0.0822 1.0000 0.0483
-11.500 -0.6390 0.06488 0.05931 -0.0808 1.0000 0.0478
-11.250 -0.6619 0.06270 0.05711 -0.0782 1.0000 0.0475
-11.000 -0.6920 0.06155 0.05597 -0.0736 1.0000 0.0473
-10.750 -0.7253 0.06118 0.05563 -0.0679 1.0000 0.0472
-10.500 -0.7586 0.06086 0.05532 -0.0620 1.0000 0.0471
-10.250 -0.7820 0.05968 0.05408 -0.0577 1.0000 0.0467
-10.000 -0.7979 0.05727 0.05148 -0.0552 0.9985 0.0463
-9.750 -0.7837 0.05245 0.04615 -0.0585 0.9903 0.0452
-9.500 -0.7633 0.04811 0.04128 -0.0614 0.9826 0.0445
-9.250 -0.7404 0.04476 0.03752 -0.0631 0.9743 0.0448
-9.000 -0.7111 0.04215 0.03452 -0.0654 0.9674 0.0472
-8.750 -0.6831 0.03999 0.03183 -0.0670 0.9592 0.0490
-8.500 -0.6403 0.03725 0.02921 -0.0699 0.9560 0.0524
-8.250 -0.6120 0.03563 0.02749 -0.0700 0.9475 0.0554
-8.000 -0.5724 0.03377 0.02571 -0.0723 0.9429 0.0625
-7.750 -0.5462 0.03238 0.02439 -0.0724 0.9347 0.0705
-7.500 -0.5156 0.03085 0.02302 -0.0737 0.9281 0.0844
-7.250 -0.4992 0.02944 0.02176 -0.0730 0.9184 0.1047
-7.000 -0.4812 0.02696 0.01970 -0.0742 0.9107 0.1492
-6.750 -0.4883 0.02366 0.01759 -0.0729 0.8985 0.2826
-6.500 -0.4439 0.02597 0.02036 -0.0736 0.8934 0.4638
-6.250 -0.4209 0.02804 0.02239 -0.0704 0.8832 0.4875
-6.000 -0.3735 0.03013 0.02435 -0.0709 0.8789 0.5118
-5.750 -0.3176 0.03269 0.02683 -0.0712 0.8765 0.5296
-5.500 -0.3002 0.03386 0.02792 -0.0679 0.8660 0.5421
-5.250 -0.2431 0.03638 0.03037 -0.0670 0.8633 0.5533
-5.000 -0.1895 0.03751 0.03134 -0.0679 0.8605 0.5673
-4.750 -0.1858 0.03709 0.03081 -0.0654 0.8491 0.5799
-4.500 -0.1333 0.03796 0.03155 -0.0660 0.8458 0.5891
-4.250 -0.1181 0.03727 0.03074 -0.0654 0.8378 0.5983
-4.000 -0.0904 0.03721 0.03056 -0.0648 0.8305 0.6047
-3.750 -0.0641 0.03569 0.02885 -0.0674 0.8255 0.6136
-3.500 -0.0570 0.03590 0.02904 -0.0637 0.8147 0.6174
-3.250 -0.0239 0.03516 0.02814 -0.0653 0.8102 0.6232
-3.000 -0.0289 0.03424 0.02711 -0.0638 0.7990 0.6296
-2.750 0.0069 0.03387 0.02665 -0.0645 0.7946 0.6327
-2.500 0.0217 0.03370 0.02643 -0.0630 0.7867 0.6363
-2.250 0.0426 0.03313 0.02575 -0.0635 0.7798 0.6408
-2.000 0.0783 0.03192 0.02433 -0.0674 0.7760 0.6459
-1.750 0.0796 0.03228 0.02470 -0.0637 0.7657 0.6483
-1.500 0.1134 0.03180 0.02413 -0.0649 0.7615 0.6512
-1.250 0.1524 0.03117 0.02338 -0.0672 0.7585 0.6545
-1.000 0.1491 0.03162 0.02383 -0.0642 0.7474 0.6584
-0.750 0.1892 0.03083 0.02286 -0.0679 0.7440 0.6627
-0.500 0.1951 0.03130 0.02336 -0.0652 0.7353 0.6647
-0.250 0.2204 0.03121 0.02324 -0.0652 0.7298 0.6676
0.000 0.2579 0.03080 0.02276 -0.0670 0.7269 0.6715
0.250 0.2571 0.03168 0.02364 -0.0644 0.7172 0.6753
0.500 0.2919 0.03135 0.02320 -0.0667 0.7128 0.6793
0.750 0.3303 0.03089 0.02271 -0.0683 0.7101 0.6821
1.000 0.3179 0.03241 0.02430 -0.0638 0.6996 0.6850
1.250 0.3514 0.03221 0.02408 -0.0649 0.6957 0.6893
1.500 0.3961 0.03165 0.02344 -0.0679 0.6934 0.6944
1.750 0.3766 0.03367 0.02551 -0.0631 0.6819 0.6976
2.000 0.4121 0.03338 0.02523 -0.0642 0.6787 0.7012
2.250 0.4565 0.03279 0.02464 -0.0665 0.6767 0.7057
2.500 0.4242 0.03553 0.02741 -0.0605 0.6640 0.7097
2.750 0.4699 0.03496 0.02684 -0.0631 0.6616 0.7150
3.000 0.5156 0.03427 0.02618 -0.0651 0.6599 0.7202
3.250 0.4714 0.03764 0.02961 -0.0579 0.6460 0.7242
3.500 0.5238 0.03678 0.02876 -0.0611 0.6444 0.7303
3.750 0.5759 0.03580 0.02784 -0.0638 0.6430 0.7358
4.000 0.5263 0.03976 0.03185 -0.0564 0.6284 0.7403
4.250 0.4996 0.04330 0.03539 -0.0528 0.6159 0.7460
4.500 0.5374 0.04271 0.03490 -0.0533 0.6128 0.7525
4.750 0.5247 0.04540 0.03762 -0.0508 0.6021 0.7592
5.000 0.5563 0.04527 0.03758 -0.0511 0.5974 0.7669
5.250 0.6044 0.04411 0.03649 -0.0525 0.5953 0.7762
5.500 0.6562 0.04252 0.03502 -0.0539 0.5940 0.7856
5.750 0.6256 0.04649 0.03902 -0.0503 0.5795 0.7943
6.000 0.6093 0.04945 0.04206 -0.0476 0.5672 0.8031
6.250 0.6509 0.04846 0.04118 -0.0481 0.5638 0.8170
6.500 0.6420 0.05103 0.04383 -0.0460 0.5520 0.8300
6.750 0.6795 0.05002 0.04298 -0.0459 0.5480 0.8482
7.000 0.7263 0.04809 0.04123 -0.0459 0.5461 0.8729
7.250 0.7753 0.04581 0.03919 -0.0459 0.5444 0.9149
7.500 0.8613 0.04192 0.03547 -0.0509 0.5446 1.0000
7.750 0.8494 0.04556 0.03911 -0.0504 0.5295 1.0000
8.000 0.9317 0.04154 0.03516 -0.0541 0.5295 1.0000
8.250 1.0371 0.03678 0.03049 -0.0610 0.5290 1.0000
8.500 1.0006 0.04030 0.03401 -0.0552 0.5145 1.0000
8.750 1.1303 0.03435 0.02818 -0.0647 0.5131 1.0000
9.000 1.0899 0.03736 0.03123 -0.0572 0.4998 1.0000
9.250 1.0859 0.03883 0.03275 -0.0541 0.4882 1.0000
9.500 1.2237 0.03230 0.02631 -0.0643 0.4821 1.0000
9.750 1.2164 0.03320 0.02729 -0.0596 0.4703 1.0000
10.000 1.2507 0.03217 0.02632 -0.0596 0.4582 1.0000
10.250 1.2853 0.03109 0.02525 -0.0596 0.4447 1.0000
10.500 1.3063 0.03058 0.02476 -0.0580 0.4301 1.0000
10.750 1.3164 0.03056 0.02476 -0.0552 0.4149 1.0000
11.000 1.3193 0.03096 0.02519 -0.0519 0.3990 1.0000
11.250 1.3181 0.03171 0.02596 -0.0485 0.3822 1.0000
11.500 1.3154 0.03273 0.02700 -0.0453 0.3642 1.0000
11.750 1.3139 0.03388 0.02812 -0.0425 0.3451 1.0000
12.000 1.3157 0.03500 0.02913 -0.0402 0.3250 1.0000
12.250 1.3128 0.03666 0.03070 -0.0378 0.3050 1.0000
12.500 1.3069 0.03872 0.03271 -0.0356 0.2854 1.0000
12.750 1.3029 0.04082 0.03470 -0.0337 0.2662 1.0000
13.000 1.3004 0.04293 0.03666 -0.0320 0.2476 1.0000
13.250 1.2972 0.04525 0.03884 -0.0306 0.2299 1.0000
13.500 1.2918 0.04788 0.04142 -0.0293 0.2134 1.0000
13.750 1.2874 0.05056 0.04404 -0.0283 0.1979 1.0000
14.000 1.2840 0.05327 0.04667 -0.0274 0.1833 1.0000
14.250 1.2816 0.05599 0.04932 -0.0267 0.1694 1.0000
14.500 1.2809 0.05864 0.05186 -0.0261 0.1562 1.0000
14.750 1.2752 0.06195 0.05527 -0.0258 0.1450 1.0000
15.000 1.2731 0.06500 0.05833 -0.0255 0.1339 1.0000
15.250 1.2737 0.06782 0.06112 -0.0252 0.1238 1.0000
15.500 1.2782 0.07025 0.06341 -0.0250 0.1138 1.0000
15.750 1.2731 0.07389 0.06722 -0.0252 0.1061 1.0000
16.000 1.2758 0.07673 0.07005 -0.0252 0.0984 1.0000
16.250 1.2778 0.07957 0.07286 -0.0253 0.0913 1.0000
16.500 1.2769 0.08304 0.07649 -0.0256 0.0854 1.0000
16.750 1.2823 0.08556 0.07893 -0.0258 0.0793 1.0000
17.000 1.2802 0.08935 0.08291 -0.0263 0.0748 1.0000
17.250 1.2782 0.09297 0.08665 -0.0271 0.0706 1.0000
17.500 1.2854 0.09555 0.08920 -0.0272 0.0659 1.0000
17.750 1.2748 0.10054 0.09447 -0.0287 0.0633 1.0000
18.000 1.2736 0.10415 0.09816 -0.0298 0.0600 1.0000
18.250 1.2784 0.10717 0.10118 -0.0303 0.0566 1.0000
18.500 1.2617 0.11329 0.10762 -0.0328 0.0553 1.0000
18.750 1.2469 0.11933 0.11393 -0.0355 0.0540 1.0000
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Polar data table (+)
Polar graphs
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