EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.84 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e554-il-1000000.txt Download as CSV file: xf-e554-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.7390 0.13829 0.13585 -0.0247 1.0000 0.0050
-18.750 -0.7574 0.13019 0.12763 -0.0288 1.0000 0.0049
-18.500 -0.7769 0.12215 0.11947 -0.0328 1.0000 0.0049
-18.250 -0.7964 0.11435 0.11153 -0.0367 1.0000 0.0050
-18.000 -0.8080 0.10829 0.10537 -0.0397 1.0000 0.0049
-17.750 -0.8194 0.10242 0.09939 -0.0426 1.0000 0.0049
-17.500 -0.8317 0.09660 0.09346 -0.0453 1.0000 0.0048
-17.250 -0.8418 0.09108 0.08783 -0.0480 1.0000 0.0051
-17.000 -0.8496 0.08646 0.08313 -0.0499 1.0000 0.0048
-16.750 -0.8556 0.08188 0.07844 -0.0520 1.0000 0.0051
-16.500 -0.8641 0.07733 0.07380 -0.0538 1.0000 0.0049
-16.250 -0.8680 0.07341 0.06978 -0.0555 1.0000 0.0050
-16.000 -0.8717 0.06963 0.06592 -0.0569 1.0000 0.0050
-15.750 -0.8744 0.06608 0.06227 -0.0582 1.0000 0.0051
-15.500 -0.8755 0.06287 0.05900 -0.0592 1.0000 0.0051
-15.250 -0.8754 0.05978 0.05582 -0.0603 1.0000 0.0052
-15.000 -0.8734 0.05705 0.05303 -0.0611 1.0000 0.0052
-14.750 -0.8759 0.05399 0.04989 -0.0618 1.0000 0.0052
-14.500 -0.8695 0.05181 0.04764 -0.0624 1.0000 0.0053
-14.250 -0.8824 0.04797 0.04369 -0.0628 1.0000 0.0055
-14.000 -0.8790 0.04578 0.04145 -0.0630 1.0000 0.0055
-13.750 -0.8851 0.04287 0.03848 -0.0631 1.0000 0.0056
-13.500 -0.8872 0.04043 0.03598 -0.0631 1.0000 0.0057
-13.250 -0.8853 0.03842 0.03392 -0.0628 1.0000 0.0058
-13.000 -0.8834 0.03646 0.03192 -0.0625 1.0000 0.0058
-12.750 -0.8829 0.03448 0.02989 -0.0619 1.0000 0.0059
-12.500 -0.8824 0.03258 0.02795 -0.0612 1.0000 0.0060
-12.250 -0.8804 0.03088 0.02621 -0.0603 1.0000 0.0061
-12.000 -0.8814 0.02907 0.02436 -0.0592 1.0000 0.0061
-11.750 -0.8816 0.02749 0.02275 -0.0578 1.0000 0.0063
-11.500 -0.8658 0.02592 0.02114 -0.0591 0.9989 0.0065
-11.250 -0.8358 0.02403 0.01919 -0.0637 0.9953 0.0066
-11.000 -0.8091 0.02235 0.01744 -0.0672 0.9896 0.0068
-10.750 -0.7951 0.02080 0.01583 -0.0681 0.9716 0.0070
-10.500 -0.7657 0.01929 0.01425 -0.0716 0.9517 0.0071
-10.250 -0.7111 0.01709 0.01193 -0.0812 0.9360 0.0076
-10.000 -0.6342 0.01581 0.01057 -0.0932 0.9163 0.0085
-9.750 -0.5893 0.01514 0.00964 -0.0981 0.8642 0.0091
-9.500 -0.5748 0.01466 0.00895 -0.0966 0.8244 0.0096
-9.250 -0.5592 0.01418 0.00833 -0.0952 0.7952 0.0103
-9.000 -0.5402 0.01381 0.00784 -0.0941 0.7725 0.0113
-8.250 -0.4771 0.01263 0.00642 -0.0920 0.7196 0.0176
-8.000 -0.4542 0.01224 0.00600 -0.0916 0.7047 0.0226
-7.750 -0.4306 0.01187 0.00561 -0.0912 0.6906 0.0294
-7.500 -0.4064 0.01154 0.00525 -0.0909 0.6770 0.0374
-7.250 -0.3821 0.01118 0.00489 -0.0907 0.6637 0.0492
-7.000 -0.3571 0.01077 0.00453 -0.0906 0.6520 0.0673
-6.750 -0.3322 0.01030 0.00414 -0.0906 0.6413 0.0935
-6.500 -0.3071 0.00983 0.00377 -0.0906 0.6305 0.1283
-6.250 -0.2819 0.00917 0.00332 -0.0907 0.6209 0.1824
-6.000 -0.2579 0.00829 0.00277 -0.0910 0.6111 0.2745
-5.750 -0.2309 0.00779 0.00251 -0.0913 0.6022 0.3450
-5.500 -0.2030 0.00768 0.00243 -0.0914 0.5929 0.3755
-5.250 -0.1742 0.00764 0.00237 -0.0916 0.5842 0.3896
-5.000 -0.1456 0.00766 0.00231 -0.0917 0.5755 0.3979
-4.750 -0.1166 0.00764 0.00227 -0.0919 0.5678 0.4055
-4.500 -0.0879 0.00770 0.00224 -0.0920 0.5600 0.4136
-4.250 -0.0589 0.00768 0.00222 -0.0922 0.5534 0.4211
-4.000 -0.0299 0.00773 0.00219 -0.0923 0.5464 0.4261
-3.750 -0.0011 0.00776 0.00217 -0.0925 0.5398 0.4325
-3.500 0.0281 0.00782 0.00222 -0.0927 0.5336 0.4408
-3.250 0.0569 0.00791 0.00222 -0.0928 0.5271 0.4449
-3.000 0.0858 0.00789 0.00217 -0.0930 0.5216 0.4476
-2.750 0.1148 0.00786 0.00212 -0.0932 0.5164 0.4506
-2.500 0.1436 0.00788 0.00210 -0.0933 0.5111 0.4530
-2.250 0.1723 0.00792 0.00210 -0.0935 0.5062 0.4555
-2.000 0.2016 0.00793 0.00208 -0.0937 0.5020 0.4580
-1.750 0.2306 0.00796 0.00207 -0.0939 0.4974 0.4603
-1.500 0.2593 0.00802 0.00207 -0.0941 0.4925 0.4621
-1.250 0.2881 0.00802 0.00205 -0.0942 0.4885 0.4647
-1.000 0.3172 0.00800 0.00205 -0.0945 0.4851 0.4678
-0.750 0.3461 0.00802 0.00206 -0.0947 0.4814 0.4706
-0.500 0.3748 0.00807 0.00208 -0.0948 0.4776 0.4731
-0.250 0.4031 0.00816 0.00211 -0.0949 0.4731 0.4755
0.000 0.4324 0.00817 0.00213 -0.0952 0.4705 0.4778
0.250 0.4615 0.00821 0.00215 -0.0954 0.4675 0.4797
0.500 0.4903 0.00821 0.00216 -0.0956 0.4643 0.4830
0.750 0.5188 0.00825 0.00220 -0.0957 0.4610 0.4862
1.000 0.5469 0.00834 0.00226 -0.0958 0.4570 0.4891
1.250 0.5758 0.00837 0.00231 -0.0960 0.4546 0.4918
1.500 0.6048 0.00841 0.00236 -0.0962 0.4522 0.4944
1.750 0.6336 0.00846 0.00240 -0.0964 0.4493 0.4967
2.000 0.6621 0.00849 0.00244 -0.0965 0.4464 0.4997
2.250 0.6903 0.00855 0.00251 -0.0966 0.4433 0.5031
2.500 0.7180 0.00867 0.00262 -0.0967 0.4396 0.5063
2.750 0.7469 0.00870 0.00268 -0.0969 0.4377 0.5097
3.000 0.7757 0.00874 0.00275 -0.0971 0.4353 0.5128
3.250 0.8042 0.00880 0.00281 -0.0972 0.4326 0.5153
3.500 0.8324 0.00884 0.00289 -0.0973 0.4297 0.5195
3.750 0.8603 0.00892 0.00298 -0.0974 0.4267 0.5231
4.000 0.8876 0.00907 0.00311 -0.0974 0.4229 0.5268
4.250 0.9162 0.00910 0.00319 -0.0975 0.4208 0.5303
4.500 0.9446 0.00914 0.00327 -0.0977 0.4178 0.5336
4.750 0.9727 0.00918 0.00336 -0.0978 0.4144 0.5385
5.000 1.0002 0.00927 0.00346 -0.0978 0.4106 0.5431
5.250 1.0269 0.00943 0.00361 -0.0977 0.4064 0.5475
5.500 1.0553 0.00946 0.00370 -0.0978 0.4038 0.5516
5.750 1.0833 0.00950 0.00381 -0.0979 0.4005 0.5569
6.000 1.1107 0.00957 0.00392 -0.0979 0.3965 0.5622
6.250 1.1371 0.00972 0.00406 -0.0977 0.3917 0.5673
6.500 1.1646 0.00979 0.00419 -0.0977 0.3879 0.5733
6.750 1.1922 0.00984 0.00431 -0.0978 0.3836 0.5799
7.000 1.2188 0.00996 0.00445 -0.0977 0.3787 0.5862
7.250 1.2447 0.01010 0.00462 -0.0974 0.3734 0.5935
7.500 1.2721 0.01016 0.00476 -0.0974 0.3681 0.6011
7.750 1.2979 0.01029 0.00492 -0.0972 0.3612 0.6088
8.000 1.3239 0.01042 0.00509 -0.0970 0.3548 0.6178
8.250 1.3493 0.01057 0.00528 -0.0967 0.3464 0.6271
8.500 1.3743 0.01075 0.00548 -0.0963 0.3375 0.6377
8.750 1.3977 0.01098 0.00573 -0.0957 0.3261 0.6486
9.000 1.4203 0.01127 0.00601 -0.0949 0.3122 0.6599
9.250 1.4412 0.01162 0.00634 -0.0939 0.2948 0.6726
9.500 1.4608 0.01203 0.00672 -0.0927 0.2767 0.6863
9.750 1.4782 0.01252 0.00718 -0.0911 0.2571 0.7016
10.000 1.4918 0.01316 0.00774 -0.0890 0.2351 0.7189
10.250 1.5024 0.01376 0.00830 -0.0863 0.2135 0.7384
10.750 1.5157 0.01512 0.00962 -0.0796 0.1773 0.7894
11.000 1.5209 0.01581 0.01035 -0.0761 0.1623 0.8301
11.250 1.5223 0.01621 0.01098 -0.0718 0.1511 1.0000
11.500 1.5268 0.01712 0.01184 -0.0688 0.1382 1.0000
11.750 1.5308 0.01811 0.01280 -0.0659 0.1271 1.0000
12.000 1.5327 0.01927 0.01393 -0.0630 0.1167 1.0000
12.250 1.5330 0.02062 0.01526 -0.0602 0.1074 1.0000
12.500 1.5342 0.02208 0.01670 -0.0579 0.0990 1.0000
12.750 1.5339 0.02377 0.01840 -0.0558 0.0909 1.0000
13.000 1.5318 0.02576 0.02039 -0.0539 0.0839 1.0000
13.250 1.5301 0.02789 0.02252 -0.0524 0.0770 1.0000
13.500 1.5286 0.03016 0.02482 -0.0512 0.0713 1.0000
13.750 1.5233 0.03289 0.02755 -0.0501 0.0651 1.0000
14.000 1.5217 0.03543 0.03013 -0.0493 0.0604 1.0000
14.250 1.5157 0.03848 0.03319 -0.0487 0.0555 1.0000
14.500 1.5106 0.04155 0.03629 -0.0482 0.0508 1.0000
14.750 1.5059 0.04469 0.03946 -0.0480 0.0471 1.0000
15.000 1.5016 0.04788 0.04270 -0.0478 0.0437 1.0000
15.250 1.4956 0.05136 0.04621 -0.0479 0.0398 1.0000
15.500 1.4919 0.05471 0.04960 -0.0481 0.0373 1.0000
15.750 1.4876 0.05821 0.05315 -0.0485 0.0347 1.0000
16.000 1.4840 0.06173 0.05671 -0.0489 0.0322 1.0000
16.250 1.4794 0.06546 0.06049 -0.0495 0.0297 1.0000
16.500 1.4771 0.06897 0.06404 -0.0502 0.0277 1.0000
16.750 1.4734 0.07273 0.06785 -0.0510 0.0258 1.0000
17.000 1.4707 0.07647 0.07163 -0.0519 0.0239 1.0000
17.250 1.4665 0.08046 0.07567 -0.0530 0.0220 1.0000
17.500 1.4654 0.08407 0.07933 -0.0540 0.0206 1.0000
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