EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 200,000 Max Cl/Cd: 72.78 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e560-il-200000.txt Download as CSV file: xf-e560-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6482 0.07146 0.06694 -0.0792 1.0000 0.0355
-13.000 -0.6719 0.06586 0.06122 -0.0819 1.0000 0.0354
-12.750 -0.6914 0.06122 0.05648 -0.0838 1.0000 0.0353
-12.500 -0.7133 0.05683 0.05197 -0.0854 1.0000 0.0354
-12.250 -0.7333 0.05314 0.04818 -0.0861 1.0000 0.0354
-12.000 -0.7522 0.05013 0.04508 -0.0857 1.0000 0.0354
-11.750 -0.7762 0.04759 0.04248 -0.0843 1.0000 0.0354
-11.500 -0.8005 0.04546 0.04031 -0.0820 1.0000 0.0353
-11.250 -0.8156 0.04260 0.03728 -0.0830 1.0000 0.0355
-11.000 -0.8205 0.04021 0.03478 -0.0825 1.0000 0.0358
-10.750 -0.8190 0.03822 0.03273 -0.0815 1.0000 0.0362
-10.500 -0.7863 0.03629 0.03080 -0.0855 0.9956 0.0374
-10.250 -0.7517 0.03435 0.02873 -0.0899 0.9904 0.0386
-10.000 -0.7165 0.03243 0.02665 -0.0940 0.9852 0.0398
-9.750 -0.6819 0.03070 0.02473 -0.0975 0.9797 0.0411
-9.500 -0.6474 0.02890 0.02285 -0.1008 0.9743 0.0427
-9.250 -0.6127 0.02737 0.02134 -0.1041 0.9687 0.0448
-8.750 -0.5378 0.02433 0.01819 -0.1113 0.9583 0.0522
-8.250 -0.4600 0.02100 0.01486 -0.1191 0.9480 0.0795
-8.000 -0.4268 0.01989 0.01376 -0.1213 0.9401 0.1030
-7.750 -0.3849 0.01914 0.01301 -0.1247 0.9358 0.1219
-7.500 -0.3472 0.01863 0.01245 -0.1270 0.9300 0.1377
-7.250 -0.3097 0.01815 0.01192 -0.1290 0.9235 0.1517
-7.000 -0.2662 0.01769 0.01140 -0.1321 0.9202 0.1667
-6.750 -0.2319 0.01735 0.01103 -0.1334 0.9124 0.1800
-6.500 -0.1914 0.01699 0.01063 -0.1358 0.9075 0.1944
-6.250 -0.1469 0.01660 0.01019 -0.1388 0.9045 0.2087
-6.000 -0.1119 0.01631 0.00979 -0.1400 0.8959 0.2207
-5.750 -0.0678 0.01595 0.00940 -0.1430 0.8909 0.2324
-5.500 -0.0198 0.01556 0.00901 -0.1467 0.8864 0.2437
-5.250 0.0170 0.01525 0.00861 -0.1483 0.8759 0.2542
-5.000 0.0607 0.01502 0.00829 -0.1512 0.8676 0.2652
-4.750 0.1009 0.01474 0.00799 -0.1534 0.8570 0.2743
-4.500 0.1372 0.01459 0.00766 -0.1549 0.8441 0.2845
-4.250 0.1730 0.01442 0.00751 -0.1562 0.8315 0.2925
-4.000 0.2089 0.01429 0.00719 -0.1576 0.8190 0.3022
-3.750 0.2409 0.01422 0.00710 -0.1582 0.8055 0.3099
-3.500 0.2702 0.01416 0.00688 -0.1583 0.7911 0.3187
-3.250 0.2986 0.01412 0.00684 -0.1582 0.7773 0.3259
-3.000 0.3283 0.01412 0.00665 -0.1584 0.7641 0.3349
-2.750 0.3571 0.01407 0.00659 -0.1583 0.7515 0.3420
-2.500 0.3857 0.01410 0.00645 -0.1583 0.7388 0.3509
-2.250 0.4120 0.01404 0.00641 -0.1578 0.7259 0.3577
-2.000 0.4399 0.01409 0.00634 -0.1576 0.7138 0.3665
-1.750 0.4685 0.01408 0.00625 -0.1576 0.7027 0.3740
-1.500 0.4946 0.01410 0.00623 -0.1571 0.6905 0.3822
-1.250 0.5218 0.01411 0.00618 -0.1569 0.6793 0.3903
-1.000 0.5502 0.01417 0.00615 -0.1568 0.6691 0.3989
-0.750 0.5760 0.01417 0.00612 -0.1563 0.6575 0.4071
-0.500 0.6032 0.01423 0.00616 -0.1560 0.6474 0.4159
-0.250 0.6308 0.01428 0.00613 -0.1558 0.6377 0.4249
0.000 0.6569 0.01434 0.00619 -0.1554 0.6274 0.4338
0.250 0.6853 0.01442 0.00618 -0.1554 0.6186 0.4433
0.500 0.7108 0.01447 0.00626 -0.1548 0.6085 0.4534
0.750 0.7386 0.01456 0.00631 -0.1547 0.6003 0.4627
1.000 0.7648 0.01464 0.00637 -0.1543 0.5908 0.4739
1.250 0.7921 0.01474 0.00647 -0.1541 0.5828 0.4843
1.500 0.8181 0.01480 0.00657 -0.1537 0.5740 0.4954
1.750 0.8462 0.01496 0.00666 -0.1536 0.5667 0.5083
2.000 0.8715 0.01503 0.00682 -0.1531 0.5582 0.5206
2.250 0.8998 0.01518 0.00693 -0.1531 0.5513 0.5343
2.500 0.9245 0.01526 0.00711 -0.1524 0.5430 0.5488
2.750 0.9523 0.01540 0.00725 -0.1524 0.5365 0.5656
3.000 0.9777 0.01552 0.00748 -0.1519 0.5292 0.5839
3.250 1.0039 0.01563 0.00764 -0.1515 0.5222 0.6049
3.500 1.0306 0.01580 0.00787 -0.1512 0.5159 0.6301
3.750 1.0549 0.01589 0.00812 -0.1505 0.5090 0.6600
4.000 1.0812 0.01601 0.00832 -0.1500 0.5032 0.6988
4.250 1.1029 0.01608 0.00863 -0.1487 0.4968 0.7512
4.500 1.1196 0.01603 0.00880 -0.1460 0.4908 0.8360
4.750 1.1421 0.01603 0.00882 -0.1446 0.4857 1.0000
5.000 1.1675 0.01632 0.00914 -0.1443 0.4792 1.0000
5.250 1.1944 0.01659 0.00937 -0.1442 0.4731 1.0000
5.500 1.2238 0.01697 0.00963 -0.1446 0.4679 1.0000
5.750 1.2469 0.01725 0.01000 -0.1438 0.4615 1.0000
6.000 1.2733 0.01754 0.01026 -0.1436 0.4558 1.0000
6.250 1.3011 0.01793 0.01058 -0.1436 0.4506 1.0000
6.500 1.3234 0.01823 0.01098 -0.1427 0.4444 1.0000
6.750 1.3494 0.01854 0.01125 -0.1424 0.4388 1.0000
7.000 1.3758 0.01894 0.01163 -0.1422 0.4335 1.0000
7.250 1.3970 0.01926 0.01205 -0.1411 0.4273 1.0000
7.500 1.4227 0.01957 0.01233 -0.1407 0.4218 1.0000
7.750 1.4466 0.01997 0.01276 -0.1401 0.4162 1.0000
8.000 1.4672 0.02030 0.01317 -0.1389 0.4099 1.0000
8.250 1.4927 0.02062 0.01345 -0.1385 0.4043 1.0000
8.500 1.5128 0.02103 0.01395 -0.1372 0.3983 1.0000
8.750 1.5328 0.02134 0.01432 -0.1359 0.3919 1.0000
9.000 1.5597 0.02173 0.01463 -0.1358 0.3861 1.0000
9.250 1.5727 0.02209 0.01517 -0.1333 0.3795 1.0000
9.500 1.5928 0.02240 0.01549 -0.1320 0.3733 1.0000
9.750 1.6118 0.02283 0.01596 -0.1306 0.3671 1.0000
10.000 1.6255 0.02320 0.01644 -0.1282 0.3604 1.0000
10.500 1.6524 0.02399 0.01735 -0.1234 0.3474 1.0000
10.750 1.6650 0.02436 0.01774 -0.1209 0.3408 1.0000
11.000 1.6747 0.02487 0.01832 -0.1181 0.3338 1.0000
11.250 1.6819 0.02537 0.01891 -0.1148 0.3267 1.0000
11.500 1.6926 0.02594 0.01950 -0.1124 0.3196 1.0000
11.750 1.6964 0.02662 0.02032 -0.1089 0.3121 1.0000
12.000 1.7060 0.02732 0.02101 -0.1065 0.3049 1.0000
12.250 1.7074 0.02824 0.02208 -0.1031 0.2969 1.0000
12.500 1.7135 0.02915 0.02300 -0.1006 0.2892 1.0000
12.750 1.7139 0.03034 0.02432 -0.0975 0.2806 1.0000
13.000 1.7160 0.03161 0.02565 -0.0949 0.2722 1.0000
13.250 1.7154 0.03311 0.02721 -0.0923 0.2630 1.0000
13.500 1.7142 0.03483 0.02903 -0.0900 0.2534 1.0000
13.750 1.7116 0.03677 0.03096 -0.0878 0.2441 1.0000
14.000 1.7075 0.03901 0.03330 -0.0858 0.2336 1.0000
14.250 1.7022 0.04153 0.03588 -0.0842 0.2231 1.0000
14.500 1.6951 0.04439 0.03875 -0.0827 0.2130 1.0000
14.750 1.6866 0.04759 0.04198 -0.0815 0.2024 1.0000
15.000 1.6782 0.05103 0.04548 -0.0807 0.1917 1.0000
15.250 1.6678 0.05485 0.04932 -0.0802 0.1816 1.0000
15.500 1.6551 0.05910 0.05357 -0.0799 0.1721 1.0000
15.750 1.6449 0.06333 0.05788 -0.0800 0.1621 1.0000
16.000 1.6335 0.06785 0.06244 -0.0803 0.1533 1.0000
16.250 1.6200 0.07278 0.06736 -0.0809 0.1450 1.0000
16.500 1.6103 0.07745 0.07212 -0.0816 0.1367 1.0000
16.750 1.5974 0.08259 0.07725 -0.0826 0.1296 1.0000
17.000 1.5881 0.08743 0.08218 -0.0837 0.1221 1.0000
17.250 1.5768 0.09258 0.08733 -0.0850 0.1159 1.0000
17.500 1.5683 0.09749 0.09234 -0.0863 0.1092 1.0000
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Polar data table (+)
Polar graphs
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