EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 500,000 Max Cl/Cd: 106.33 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e552-il-500000.txt Download as CSV file: xf-e552-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6635 0.10124 0.09812 -0.0493 1.0000 0.0095
-16.000 -0.6796 0.09404 0.09079 -0.0535 1.0000 0.0094
-15.750 -0.6923 0.08792 0.08454 -0.0570 1.0000 0.0094
-15.500 -0.7031 0.08261 0.07913 -0.0593 1.0000 0.0093
-15.250 -0.7220 0.07611 0.07245 -0.0629 1.0000 0.0093
-15.000 -0.7347 0.07099 0.06719 -0.0651 1.0000 0.0093
-14.750 -0.7477 0.06604 0.06208 -0.0672 1.0000 0.0093
-14.500 -0.7572 0.06184 0.05773 -0.0689 1.0000 0.0093
-14.250 -0.7649 0.05801 0.05377 -0.0699 1.0000 0.0092
-14.000 -0.7729 0.05453 0.05012 -0.0712 1.0000 0.0093
-13.750 -0.7774 0.05133 0.04679 -0.0714 1.0000 0.0093
-13.500 -0.7812 0.04850 0.04381 -0.0720 1.0000 0.0094
-13.250 -0.7802 0.04603 0.04124 -0.0717 1.0000 0.0093
-13.000 -0.7817 0.04350 0.03856 -0.0716 1.0000 0.0094
-12.750 -0.7788 0.04137 0.03632 -0.0710 1.0000 0.0095
-12.500 -0.7751 0.03935 0.03421 -0.0699 1.0000 0.0096
-12.250 -0.7699 0.03763 0.03243 -0.0688 1.0000 0.0097
-12.000 -0.7645 0.03604 0.03081 -0.0678 1.0000 0.0098
-11.750 -0.7590 0.03452 0.02925 -0.0666 1.0000 0.0099
-11.500 -0.7537 0.03310 0.02779 -0.0654 1.0000 0.0101
-11.250 -0.7486 0.03175 0.02642 -0.0641 1.0000 0.0102
-11.000 -0.7444 0.03045 0.02509 -0.0626 1.0000 0.0104
-10.500 -0.7022 0.02738 0.02193 -0.0659 0.9781 0.0109
-10.250 -0.6611 0.02564 0.02011 -0.0714 0.9454 0.0113
-10.000 -0.5897 0.02353 0.01785 -0.0833 0.9225 0.0123
-9.750 -0.5277 0.02133 0.01544 -0.0944 0.8730 0.0135
-9.500 -0.5144 0.02029 0.01415 -0.0943 0.8258 0.0140
-9.250 -0.5106 0.01926 0.01292 -0.0923 0.7946 0.0147
-9.000 -0.5098 0.01842 0.01191 -0.0896 0.7704 0.0150
-8.750 -0.5058 0.01747 0.01079 -0.0873 0.7511 0.0159
-8.500 -0.4933 0.01680 0.01002 -0.0857 0.7345 0.0171
-8.250 -0.4773 0.01621 0.00931 -0.0845 0.7198 0.0193
-8.000 -0.4612 0.01553 0.00857 -0.0833 0.7066 0.0224
-7.750 -0.4429 0.01490 0.00789 -0.0824 0.6947 0.0281
-7.500 -0.4238 0.01429 0.00724 -0.0815 0.6838 0.0375
-7.250 -0.4028 0.01373 0.00670 -0.0810 0.6732 0.0515
-7.000 -0.3814 0.01314 0.00618 -0.0805 0.6637 0.0744
-6.750 -0.3601 0.01249 0.00565 -0.0801 0.6546 0.1093
-6.500 -0.3388 0.01165 0.00505 -0.0799 0.6458 0.1666
-6.250 -0.3201 0.01038 0.00422 -0.0796 0.6380 0.2792
-6.000 -0.2966 0.00970 0.00395 -0.0796 0.6301 0.3874
-5.750 -0.2687 0.00973 0.00391 -0.0797 0.6229 0.4170
-5.500 -0.2403 0.00979 0.00392 -0.0797 0.6162 0.4339
-5.250 -0.2118 0.00987 0.00392 -0.0798 0.6096 0.4452
-5.000 -0.1835 0.00995 0.00390 -0.0799 0.6039 0.4530
-4.750 -0.1546 0.01004 0.00391 -0.0800 0.5979 0.4614
-4.500 -0.1262 0.01013 0.00395 -0.0800 0.5924 0.4693
-4.250 -0.0976 0.01025 0.00397 -0.0801 0.5872 0.4759
-4.000 -0.0688 0.01028 0.00394 -0.0803 0.5820 0.4816
-3.750 -0.0404 0.01048 0.00413 -0.0803 0.5773 0.4907
-3.500 -0.0119 0.01064 0.00417 -0.0803 0.5730 0.4979
-3.250 0.0169 0.01058 0.00412 -0.0805 0.5690 0.5004
-3.000 0.0458 0.01056 0.00406 -0.0807 0.5649 0.5026
-2.750 0.0746 0.01056 0.00399 -0.0810 0.5611 0.5049
-2.500 0.1034 0.01061 0.00393 -0.0812 0.5574 0.5073
-2.250 0.1324 0.01058 0.00387 -0.0815 0.5539 0.5094
-2.000 0.1615 0.01058 0.00381 -0.0817 0.5502 0.5113
-1.750 0.1902 0.01052 0.00372 -0.0820 0.5469 0.5135
-1.500 0.2189 0.01052 0.00369 -0.0822 0.5438 0.5157
-1.250 0.2479 0.01058 0.00370 -0.0825 0.5408 0.5178
-1.000 0.2767 0.01057 0.00369 -0.0827 0.5381 0.5200
-0.750 0.3056 0.01057 0.00368 -0.0830 0.5350 0.5222
-0.500 0.3345 0.01059 0.00367 -0.0832 0.5320 0.5246
-0.250 0.3635 0.01064 0.00366 -0.0835 0.5292 0.5269
0.000 0.3924 0.01069 0.00366 -0.0838 0.5266 0.5293
0.250 0.4212 0.01072 0.00371 -0.0841 0.5241 0.5318
0.500 0.4499 0.01073 0.00375 -0.0843 0.5217 0.5341
0.750 0.4786 0.01075 0.00379 -0.0845 0.5189 0.5367
1.000 0.5073 0.01079 0.00382 -0.0847 0.5162 0.5394
1.250 0.5362 0.01085 0.00386 -0.0850 0.5139 0.5421
1.500 0.5652 0.01095 0.00391 -0.0853 0.5115 0.5446
1.750 0.5940 0.01103 0.00401 -0.0856 0.5090 0.5476
2.000 0.6223 0.01105 0.00409 -0.0858 0.5067 0.5506
2.250 0.6507 0.01110 0.00418 -0.0860 0.5043 0.5538
2.500 0.6792 0.01116 0.00426 -0.0862 0.5017 0.5571
2.750 0.7079 0.01123 0.00432 -0.0865 0.4992 0.5602
3.000 0.7363 0.01128 0.00440 -0.0867 0.4968 0.5635
3.250 0.7652 0.01144 0.00455 -0.0870 0.4941 0.5669
3.500 0.7931 0.01149 0.00467 -0.0871 0.4918 0.5706
3.750 0.8210 0.01155 0.00478 -0.0872 0.4890 0.5747
4.000 0.8489 0.01159 0.00487 -0.0873 0.4859 0.5787
4.250 0.8769 0.01163 0.00496 -0.0874 0.4829 0.5830
4.500 0.9051 0.01173 0.00507 -0.0876 0.4800 0.5875
4.750 0.9333 0.01189 0.00524 -0.0878 0.4770 0.5923
5.000 0.9602 0.01190 0.00537 -0.0878 0.4740 0.5968
5.250 0.9874 0.01194 0.00548 -0.0878 0.4705 0.6019
5.500 1.0148 0.01199 0.00556 -0.0878 0.4669 0.6076
5.750 1.0426 0.01211 0.00569 -0.0879 0.4633 0.6131
6.000 1.0690 0.01217 0.00586 -0.0878 0.4598 0.6194
6.250 1.0955 0.01221 0.00598 -0.0876 0.4558 0.6264
6.500 1.1220 0.01224 0.00610 -0.0875 0.4518 0.6333
6.750 1.1491 0.01237 0.00622 -0.0875 0.4477 0.6413
7.000 1.1744 0.01239 0.00640 -0.0871 0.4432 0.6489
7.250 1.2000 0.01243 0.00652 -0.0868 0.4382 0.6579
7.500 1.2254 0.01248 0.00664 -0.0865 0.4331 0.6670
7.750 1.2504 0.01255 0.00682 -0.0861 0.4277 0.6772
8.000 1.2750 0.01259 0.00696 -0.0857 0.4215 0.6889
8.250 1.2990 0.01269 0.00713 -0.0851 0.4154 0.7013
8.500 1.3229 0.01272 0.00732 -0.0845 0.4077 0.7153
8.750 1.3455 0.01283 0.00750 -0.0837 0.3999 0.7307
9.000 1.3677 0.01292 0.00771 -0.0828 0.3895 0.7482
9.250 1.3887 0.01306 0.00795 -0.0818 0.3776 0.7684
9.500 1.4071 0.01325 0.00823 -0.0802 0.3628 0.7922
9.750 1.4214 0.01354 0.00858 -0.0780 0.3446 0.8237
10.000 1.4282 0.01386 0.00899 -0.0743 0.3257 0.8775
10.250 1.4336 0.01428 0.00944 -0.0705 0.3047 1.0000
10.500 1.4380 0.01508 0.01013 -0.0671 0.2838 1.0000
10.750 1.4420 0.01595 0.01093 -0.0638 0.2642 1.0000
11.000 1.4440 0.01695 0.01186 -0.0604 0.2456 1.0000
11.250 1.4442 0.01811 0.01297 -0.0571 0.2289 1.0000
11.500 1.4426 0.01948 0.01429 -0.0541 0.2132 1.0000
11.750 1.4390 0.02114 0.01590 -0.0512 0.1979 1.0000
12.000 1.4363 0.02295 0.01769 -0.0489 0.1845 1.0000
12.250 1.4321 0.02506 0.01977 -0.0469 0.1714 1.0000
12.500 1.4265 0.02748 0.02216 -0.0452 0.1585 1.0000
12.750 1.4201 0.03013 0.02479 -0.0438 0.1464 1.0000
13.000 1.4143 0.03289 0.02755 -0.0427 0.1366 1.0000
13.250 1.4076 0.03582 0.03046 -0.0418 0.1258 1.0000
13.500 1.4034 0.03863 0.03328 -0.0411 0.1165 1.0000
13.750 1.3973 0.04168 0.03633 -0.0405 0.1077 1.0000
14.000 1.3913 0.04482 0.03946 -0.0400 0.0998 1.0000
14.250 1.3880 0.04779 0.04245 -0.0398 0.0923 1.0000
14.500 1.3826 0.05108 0.04575 -0.0397 0.0856 1.0000
14.750 1.3818 0.05398 0.04868 -0.0397 0.0796 1.0000
15.000 1.3772 0.05736 0.05206 -0.0398 0.0737 1.0000
15.250 1.3765 0.06039 0.05513 -0.0400 0.0683 1.0000
15.500 1.3725 0.06388 0.05862 -0.0404 0.0626 1.0000
15.750 1.3724 0.06697 0.06175 -0.0408 0.0580 1.0000
16.000 1.3677 0.07070 0.06549 -0.0414 0.0535 1.0000
16.250 1.3690 0.07374 0.06859 -0.0419 0.0494 1.0000
16.500 1.3650 0.07754 0.07238 -0.0427 0.0453 1.0000
16.750 1.3652 0.08083 0.07573 -0.0434 0.0419 1.0000
17.000 1.3633 0.08446 0.07939 -0.0443 0.0387 1.0000
17.250 1.3584 0.08860 0.08357 -0.0454 0.0361 1.0000
17.500 1.3611 0.09170 0.08673 -0.0463 0.0334 1.0000
17.750 1.3582 0.09567 0.09076 -0.0475 0.0315 1.0000
18.000 1.3535 0.09995 0.09507 -0.0489 0.0293 1.0000
18.250 1.3550 0.10335 0.09855 -0.0501 0.0273 1.0000
18.500 1.3526 0.10739 0.10263 -0.0516 0.0253 1.0000
18.750 1.3469 0.11200 0.10730 -0.0533 0.0237 1.0000
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