EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 100,000 Max Cl/Cd: 31.16 at α=12.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e552-il-100000.txt Download as CSV file: xf-e552-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 552 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 -0.3842 0.13438 0.12946 -0.0406 1.0000 0.1301
-12.750 -0.5157 0.08938 0.08423 -0.0660 1.0000 0.0516
-12.500 -0.5300 0.08361 0.07844 -0.0682 1.0000 0.0509
-12.250 -0.5480 0.07803 0.07281 -0.0705 1.0000 0.0501
-12.000 -0.5715 0.07258 0.06727 -0.0728 1.0000 0.0494
-11.750 -0.5955 0.06774 0.06232 -0.0745 1.0000 0.0489
-11.500 -0.6179 0.06341 0.05787 -0.0752 1.0000 0.0481
-11.250 -0.6404 0.05968 0.05400 -0.0751 1.0000 0.0475
-11.000 -0.6641 0.05646 0.05063 -0.0738 1.0000 0.0468
-10.750 -0.6886 0.05405 0.04808 -0.0709 1.0000 0.0462
-10.500 -0.7109 0.05183 0.04571 -0.0672 1.0000 0.0457
-10.250 -0.7299 0.04995 0.04371 -0.0631 1.0000 0.0454
-10.000 -0.7566 0.04933 0.04307 -0.0572 1.0000 0.0453
-9.750 -0.7512 0.04750 0.04111 -0.0573 0.9945 0.0462
-9.500 -0.7148 0.04381 0.03700 -0.0625 0.9830 0.0481
-9.250 -0.6781 0.04028 0.03301 -0.0665 0.9708 0.0497
-9.000 -0.6373 0.03720 0.02951 -0.0698 0.9594 0.0511
-8.750 -0.5933 0.03413 0.02640 -0.0725 0.9500 0.0543
-8.500 -0.5462 0.03214 0.02428 -0.0765 0.9413 0.0613
-8.250 -0.4999 0.02992 0.02223 -0.0792 0.9322 0.0714
-8.000 -0.4590 0.02810 0.02049 -0.0817 0.9203 0.0871
-7.750 -0.4283 0.02612 0.01880 -0.0836 0.9058 0.1132
-7.500 -0.4136 0.02374 0.01679 -0.0846 0.8876 0.1561
-7.250 -0.4183 0.02038 0.01452 -0.0842 0.8686 0.2831
-7.000 -0.3910 0.02219 0.01673 -0.0825 0.8532 0.4445
-6.750 -0.3549 0.02458 0.01898 -0.0808 0.8400 0.4747
-6.500 -0.3221 0.02640 0.02059 -0.0793 0.8278 0.4965
-6.250 -0.2855 0.02866 0.02272 -0.0771 0.8164 0.5127
-6.000 -0.2408 0.03190 0.02592 -0.0735 0.8046 0.5222
-5.750 -0.2055 0.03354 0.02739 -0.0713 0.7942 0.5336
-5.500 -0.1798 0.03408 0.02774 -0.0698 0.7846 0.5470
-5.250 -0.1625 0.03418 0.02770 -0.0683 0.7746 0.5611
-5.000 -0.1087 0.03643 0.02978 -0.0660 0.7673 0.5681
-4.750 -0.0976 0.03594 0.02920 -0.0645 0.7578 0.5799
-4.500 -0.0676 0.03612 0.02920 -0.0636 0.7510 0.5884
-4.250 -0.0552 0.03556 0.02856 -0.0624 0.7425 0.5968
-4.000 -0.0303 0.03536 0.02822 -0.0617 0.7363 0.6035
-3.750 -0.0237 0.03428 0.02706 -0.0613 0.7298 0.6115
-3.500 0.0021 0.03429 0.02699 -0.0603 0.7233 0.6160
-3.250 0.0197 0.03347 0.02599 -0.0605 0.7184 0.6222
-3.000 0.0306 0.03266 0.02514 -0.0603 0.7115 0.6276
-2.750 0.0544 0.03248 0.02488 -0.0596 0.7060 0.6310
-2.500 0.0783 0.03201 0.02426 -0.0599 0.7019 0.6354
-2.250 0.0915 0.03132 0.02353 -0.0605 0.6960 0.6402
-2.000 0.1127 0.03090 0.02303 -0.0607 0.6910 0.6439
-1.750 0.1384 0.03067 0.02270 -0.0606 0.6870 0.6466
-1.500 0.1583 0.03054 0.02256 -0.0604 0.6820 0.6499
-1.250 0.1788 0.03031 0.02228 -0.0609 0.6767 0.6540
-1.000 0.2060 0.02979 0.02161 -0.0631 0.6729 0.6581
-0.750 0.2326 0.02967 0.02142 -0.0631 0.6699 0.6605
-0.500 0.2480 0.03002 0.02184 -0.0620 0.6645 0.6636
-0.250 0.2698 0.03011 0.02191 -0.0621 0.6598 0.6671
0.000 0.2983 0.02992 0.02163 -0.0633 0.6563 0.6707
0.250 0.3301 0.02972 0.02129 -0.0654 0.6536 0.6747
0.500 0.3399 0.03051 0.02222 -0.0636 0.6482 0.6774
0.750 0.3590 0.03090 0.02265 -0.0631 0.6435 0.6808
1.000 0.3871 0.03094 0.02263 -0.0638 0.6402 0.6848
1.250 0.4206 0.03085 0.02244 -0.0656 0.6378 0.6890
1.500 0.4250 0.03218 0.02390 -0.0642 0.6318 0.6922
1.750 0.4400 0.03290 0.02469 -0.0632 0.6269 0.6956
2.000 0.4673 0.03310 0.02487 -0.0636 0.6239 0.7002
2.250 0.5032 0.03302 0.02471 -0.0653 0.6216 0.7055
2.500 0.4817 0.03594 0.02783 -0.0617 0.6130 0.7086
2.750 0.5027 0.03651 0.02843 -0.0613 0.6092 0.7125
3.000 0.5375 0.03639 0.02830 -0.0624 0.6067 0.7177
3.250 0.4886 0.04123 0.03326 -0.0575 0.5962 0.7218
3.500 0.5144 0.04154 0.03363 -0.0574 0.5926 0.7265
3.750 0.5592 0.04086 0.03296 -0.0588 0.5906 0.7328
4.000 0.6106 0.03990 0.03197 -0.0611 0.5891 0.7396
4.250 0.5185 0.04716 0.03936 -0.0530 0.5752 0.7423
4.500 0.4839 0.05149 0.04374 -0.0502 0.5664 0.7467
4.750 0.5082 0.05218 0.04445 -0.0506 0.5611 0.7539
5.000 0.5533 0.05132 0.04368 -0.0511 0.5584 0.7613
5.250 0.5158 0.05593 0.04833 -0.0487 0.5482 0.7670
5.500 0.5515 0.05569 0.04817 -0.0489 0.5439 0.7759
5.750 0.5921 0.05535 0.04787 -0.0495 0.5401 0.7866
6.000 0.5639 0.05922 0.05182 -0.0475 0.5295 0.7933
6.250 0.6143 0.05801 0.05070 -0.0481 0.5264 0.8057
6.500 0.5862 0.06212 0.05488 -0.0465 0.5148 0.8151
6.750 0.6307 0.06105 0.05391 -0.0464 0.5112 0.8312
7.000 0.6112 0.06451 0.05747 -0.0450 0.4999 0.8448
7.250 0.6489 0.06354 0.05667 -0.0442 0.4958 0.8696
7.500 0.6996 0.06145 0.05480 -0.0436 0.4938 0.9166
7.750 0.6868 0.06536 0.05879 -0.0449 0.4801 1.0000
8.000 0.6865 0.06862 0.06205 -0.0465 0.4680 1.0000
8.250 0.7396 0.06742 0.06084 -0.0481 0.4642 1.0000
8.500 0.7333 0.07081 0.06424 -0.0484 0.4518 1.0000
8.750 0.7835 0.06925 0.06271 -0.0489 0.4484 1.0000
11.250 0.9443 0.07879 0.07279 -0.0459 0.3612 1.0000
11.500 1.0005 0.07412 0.06827 -0.0443 0.3591 1.0000
11.750 1.0651 0.06787 0.06218 -0.0423 0.3584 1.0000
12.000 1.1483 0.05913 0.05363 -0.0400 0.3589 1.0000
12.250 1.3169 0.04251 0.03717 -0.0391 0.3551 1.0000
12.500 1.3295 0.04267 0.03734 -0.0378 0.3402 1.0000
12.750 1.3329 0.04383 0.03850 -0.0365 0.3242 1.0000
13.000 1.3347 0.04532 0.03996 -0.0353 0.3074 1.0000
13.250 1.3370 0.04691 0.04149 -0.0342 0.2898 1.0000
13.500 1.3400 0.04854 0.04301 -0.0332 0.2721 1.0000
13.750 1.3442 0.05016 0.04447 -0.0322 0.2544 1.0000
14.000 1.3433 0.05242 0.04661 -0.0314 0.2378 1.0000
14.250 1.3379 0.05528 0.04940 -0.0308 0.2226 1.0000
14.500 1.3338 0.05814 0.05218 -0.0304 0.2080 1.0000
14.750 1.3308 0.06097 0.05492 -0.0301 0.1940 1.0000
15.000 1.3250 0.06428 0.05822 -0.0301 0.1813 1.0000
15.250 1.3181 0.06787 0.06185 -0.0303 0.1695 1.0000
15.500 1.3143 0.07120 0.06516 -0.0305 0.1580 1.0000
15.750 1.3132 0.07425 0.06817 -0.0306 0.1471 1.0000
16.000 1.3154 0.07692 0.07071 -0.0306 0.1365 1.0000
16.250 1.3105 0.08066 0.07452 -0.0313 0.1275 1.0000
16.500 1.3082 0.08417 0.07808 -0.0318 0.1192 1.0000
16.750 1.3146 0.08641 0.08019 -0.0318 0.1102 1.0000
17.000 1.3052 0.09110 0.08509 -0.0331 0.1041 1.0000
17.250 1.3116 0.09346 0.08736 -0.0332 0.0967 1.0000
17.500 1.3025 0.09821 0.09231 -0.0348 0.0917 1.0000
17.750 1.3127 0.10007 0.09402 -0.0347 0.0850 1.0000
18.000 1.2995 0.10560 0.09985 -0.0368 0.0814 1.0000
18.250 1.3068 0.10781 0.10195 -0.0374 0.0758 1.0000
18.500 1.3006 0.11243 0.10674 -0.0389 0.0723 1.0000
18.750 1.2860 0.11843 0.11301 -0.0417 0.0697 1.0000
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Polar data table (+)
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