EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 200,000 Max Cl/Cd: 67.04 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e550-il-200000-n5.txt Download as CSV file: xf-e550-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5122 0.12495 0.12110 -0.0335 1.0000 0.0097
-15.000 -0.5638 0.10611 0.10213 -0.0426 1.0000 0.0094
-14.750 -0.5969 0.09378 0.08962 -0.0499 1.0000 0.0092
-14.500 -0.6221 0.08472 0.08039 -0.0552 1.0000 0.0090
-14.250 -0.6457 0.07702 0.07249 -0.0594 1.0000 0.0090
-14.000 -0.6668 0.07054 0.06580 -0.0624 1.0000 0.0090
-13.750 -0.6857 0.06497 0.06000 -0.0645 1.0000 0.0090
-13.500 -0.6992 0.06057 0.05540 -0.0656 1.0000 0.0090
-13.250 -0.7110 0.05656 0.05118 -0.0662 1.0000 0.0091
-13.000 -0.7196 0.05305 0.04746 -0.0664 1.0000 0.0092
-12.750 -0.7252 0.04997 0.04419 -0.0662 1.0000 0.0092
-12.500 -0.7277 0.04733 0.04133 -0.0658 1.0000 0.0094
-12.250 -0.7293 0.04472 0.03849 -0.0650 1.0000 0.0096
-12.000 -0.7277 0.04263 0.03626 -0.0642 1.0000 0.0099
-11.750 -0.7230 0.04078 0.03430 -0.0632 1.0000 0.0099
-11.500 -0.7187 0.03957 0.03313 -0.0626 1.0000 0.0105
-11.250 -0.7123 0.03795 0.03140 -0.0613 1.0000 0.0106
-11.000 -0.7044 0.03643 0.02978 -0.0599 1.0000 0.0107
-10.750 -0.6972 0.03514 0.02841 -0.0585 1.0000 0.0111
-10.500 -0.6886 0.03382 0.02698 -0.0569 1.0000 0.0115
-10.250 -0.6671 0.03219 0.02523 -0.0573 0.9856 0.0119
-10.000 -0.6295 0.03048 0.02336 -0.0610 0.9387 0.0124
-9.750 -0.5742 0.02860 0.02137 -0.0688 0.9028 0.0130
-9.500 -0.5235 0.02697 0.01951 -0.0756 0.8619 0.0141
-9.250 -0.4938 0.02577 0.01805 -0.0780 0.8241 0.0150
-9.000 -0.4756 0.02478 0.01689 -0.0781 0.7953 0.0156
-8.750 -0.4623 0.02391 0.01590 -0.0771 0.7730 0.0169
-8.500 -0.4488 0.02318 0.01502 -0.0760 0.7543 0.0188
-8.250 -0.4382 0.02234 0.01409 -0.0744 0.7381 0.0203
-8.000 -0.4274 0.02157 0.01319 -0.0728 0.7238 0.0225
-7.500 -0.4133 0.02006 0.01152 -0.0681 0.6982 0.0276
-7.250 -0.4031 0.01946 0.01084 -0.0660 0.6871 0.0323
-6.750 -0.3777 0.01821 0.00954 -0.0625 0.6671 0.0498
-6.500 -0.3632 0.01760 0.00895 -0.0610 0.6588 0.0664
-6.250 -0.3480 0.01693 0.00837 -0.0597 0.6504 0.0915
-6.000 -0.3330 0.01620 0.00777 -0.0584 0.6432 0.1307
-5.750 -0.3191 0.01525 0.00711 -0.0571 0.6358 0.1940
-5.500 -0.3088 0.01390 0.00627 -0.0556 0.6291 0.3108
-5.250 -0.2943 0.01312 0.00630 -0.0539 0.6225 0.4740
-5.000 -0.2678 0.01327 0.00639 -0.0535 0.6155 0.5172
-4.750 -0.2407 0.01344 0.00639 -0.0533 0.6096 0.5388
-4.500 -0.2131 0.01361 0.00645 -0.0532 0.6033 0.5545
-4.250 -0.1857 0.01382 0.00652 -0.0529 0.5977 0.5678
-4.000 -0.1582 0.01422 0.00685 -0.0524 0.5931 0.5810
-3.750 -0.1306 0.01470 0.00733 -0.0518 0.5877 0.5946
-3.500 -0.1033 0.01487 0.00737 -0.0516 0.5827 0.6035
-3.250 -0.0755 0.01488 0.00726 -0.0516 0.5783 0.6057
-3.000 -0.0475 0.01484 0.00714 -0.0517 0.5736 0.6078
-2.750 -0.0196 0.01478 0.00698 -0.0519 0.5688 0.6099
-2.500 0.0084 0.01473 0.00680 -0.0521 0.5647 0.6122
-2.250 0.0365 0.01468 0.00660 -0.0524 0.5613 0.6146
-2.000 0.0648 0.01460 0.00642 -0.0527 0.5576 0.6168
-1.750 0.0931 0.01454 0.00627 -0.0531 0.5537 0.6187
-1.500 0.1211 0.01452 0.00621 -0.0532 0.5499 0.6201
-1.250 0.1491 0.01453 0.00614 -0.0533 0.5465 0.6216
-1.000 0.1773 0.01453 0.00607 -0.0535 0.5433 0.6231
-0.750 0.2055 0.01452 0.00604 -0.0538 0.5397 0.6246
-0.500 0.2337 0.01452 0.00600 -0.0540 0.5364 0.6263
-0.250 0.2619 0.01453 0.00596 -0.0543 0.5334 0.6283
0.000 0.2903 0.01456 0.00591 -0.0546 0.5307 0.6304
0.500 0.3472 0.01461 0.00585 -0.0553 0.5248 0.6344
0.750 0.3752 0.01463 0.00587 -0.0555 0.5215 0.6359
1.000 0.4032 0.01467 0.00592 -0.0557 0.5187 0.6372
1.250 0.4312 0.01472 0.00597 -0.0559 0.5161 0.6387
1.500 0.4594 0.01480 0.00601 -0.0561 0.5136 0.6404
1.750 0.4876 0.01488 0.00608 -0.0563 0.5111 0.6424
2.000 0.5152 0.01495 0.00619 -0.0565 0.5080 0.6445
2.250 0.5431 0.01503 0.00629 -0.0567 0.5052 0.6467
2.500 0.5711 0.01511 0.00638 -0.0570 0.5024 0.6487
2.750 0.5993 0.01519 0.00645 -0.0573 0.4997 0.6508
3.000 0.6274 0.01528 0.00653 -0.0575 0.4973 0.6526
3.250 0.6553 0.01540 0.00666 -0.0577 0.4950 0.6542
3.500 0.6821 0.01550 0.00687 -0.0578 0.4919 0.6560
3.750 0.7091 0.01561 0.00705 -0.0578 0.4888 0.6581
4.000 0.7364 0.01572 0.00721 -0.0579 0.4858 0.6605
4.250 0.7639 0.01584 0.00735 -0.0581 0.4829 0.6631
4.500 0.7920 0.01596 0.00747 -0.0583 0.4803 0.6658
4.750 0.8189 0.01611 0.00767 -0.0584 0.4771 0.6683
5.000 0.8447 0.01622 0.00791 -0.0583 0.4732 0.6703
5.250 0.8709 0.01633 0.00810 -0.0582 0.4695 0.6724
5.500 0.8977 0.01643 0.00826 -0.0582 0.4660 0.6748
5.750 0.9249 0.01656 0.00842 -0.0583 0.4627 0.6775
6.000 0.9496 0.01671 0.00871 -0.0580 0.4582 0.6804
6.250 0.9752 0.01683 0.00892 -0.0578 0.4537 0.6836
6.500 1.0013 0.01693 0.00906 -0.0577 0.4496 0.6865
6.750 1.0262 0.01706 0.00930 -0.0574 0.4450 0.6894
7.000 1.0498 0.01719 0.00958 -0.0569 0.4394 0.6928
7.250 1.0746 0.01728 0.00974 -0.0565 0.4342 0.6963
7.500 1.0987 0.01742 0.00997 -0.0561 0.4285 0.7001
7.750 1.1213 0.01756 0.01025 -0.0554 0.4219 0.7034
8.000 1.1450 0.01765 0.01039 -0.0549 0.4161 0.7068
8.250 1.1659 0.01783 0.01077 -0.0539 0.4081 0.7108
8.500 1.1880 0.01795 0.01094 -0.0531 0.4008 0.7152
8.750 1.2076 0.01815 0.01130 -0.0520 0.3912 0.7196
9.000 1.2265 0.01833 0.01159 -0.0507 0.3815 0.7242
9.250 1.2436 0.01855 0.01187 -0.0491 0.3700 0.7297
9.500 1.2588 0.01884 0.01225 -0.0473 0.3562 0.7355
9.750 1.2697 0.01917 0.01264 -0.0448 0.3409 0.7411
10.000 1.2761 0.01962 0.01311 -0.0416 0.3245 0.7479
10.250 1.2803 0.02027 0.01377 -0.0383 0.3065 0.7546
10.500 1.2810 0.02112 0.01462 -0.0347 0.2881 0.7624
10.750 1.2792 0.02222 0.01570 -0.0313 0.2705 0.7710
11.000 1.2751 0.02358 0.01707 -0.0281 0.2538 0.7814
11.250 1.2702 0.02517 0.01869 -0.0253 0.2384 0.7932
11.500 1.2649 0.02700 0.02055 -0.0229 0.2240 0.8078
11.750 1.2590 0.02904 0.02265 -0.0209 0.2102 0.8274
12.000 1.2526 0.03119 0.02490 -0.0190 0.1975 0.8573
12.500 1.2402 0.03617 0.03000 -0.0169 0.1734 1.0000
12.750 1.2349 0.03902 0.03283 -0.0164 0.1620 1.0000
13.000 1.2313 0.04179 0.03560 -0.0161 0.1509 1.0000
13.250 1.2274 0.04466 0.03848 -0.0159 0.1409 1.0000
13.500 1.2225 0.04771 0.04152 -0.0158 0.1316 1.0000
13.750 1.2196 0.05067 0.04450 -0.0158 0.1224 1.0000
14.000 1.2180 0.05359 0.04744 -0.0160 0.1142 1.0000
14.250 1.2140 0.05685 0.05069 -0.0163 0.1065 1.0000
14.500 1.2138 0.05978 0.05365 -0.0167 0.0985 1.0000
14.750 1.2120 0.06296 0.05685 -0.0171 0.0917 1.0000
15.000 1.2104 0.06619 0.06010 -0.0177 0.0846 1.0000
15.250 1.2098 0.06937 0.06332 -0.0183 0.0786 1.0000
15.500 1.2080 0.07277 0.06673 -0.0191 0.0727 1.0000
15.750 1.2077 0.07605 0.07008 -0.0199 0.0674 1.0000
16.000 1.2057 0.07961 0.07366 -0.0208 0.0623 1.0000
16.250 1.2055 0.08299 0.07710 -0.0218 0.0578 1.0000
16.500 1.2039 0.08663 0.08078 -0.0229 0.0536 1.0000
16.750 1.2028 0.09026 0.08446 -0.0241 0.0500 1.0000
17.000 1.2017 0.09393 0.08820 -0.0253 0.0464 1.0000
17.250 1.1981 0.09803 0.09233 -0.0268 0.0434 1.0000
17.500 1.1986 0.10159 0.09599 -0.0281 0.0404 1.0000
17.750 1.1960 0.10566 0.10011 -0.0297 0.0379 1.0000
18.000 1.1935 0.10978 0.10430 -0.0314 0.0357 1.0000
18.250 1.1927 0.11366 0.10829 -0.0330 0.0335 1.0000
18.500 1.1892 0.11801 0.11269 -0.0350 0.0314 1.0000
18.750 1.1865 0.12229 0.11705 -0.0369 0.0297 1.0000
19.000 1.1854 0.12635 0.12122 -0.0389 0.0280 1.0000
19.250 1.1821 0.13080 0.12574 -0.0411 0.0264 1.0000
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Polar data table (+)
Polar graphs
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