EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.51 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e554-il-1000000-n5.txt Download as CSV file: xf-e554-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.8120 0.13684 0.13407 -0.0249 1.0000 0.0031
-19.500 -0.8334 0.12858 0.12569 -0.0291 1.0000 0.0031
-19.250 -0.8513 0.12127 0.11827 -0.0327 1.0000 0.0032
-19.000 -0.8686 0.11421 0.11110 -0.0362 1.0000 0.0032
-18.750 -0.8829 0.10788 0.10467 -0.0393 1.0000 0.0032
-18.500 -0.8985 0.10150 0.09818 -0.0424 1.0000 0.0032
-18.250 -0.9097 0.09597 0.09255 -0.0450 1.0000 0.0033
-18.000 -0.9203 0.09069 0.08718 -0.0474 1.0000 0.0032
-17.750 -0.9276 0.08607 0.08247 -0.0495 1.0000 0.0032
-17.500 -0.9374 0.08115 0.07745 -0.0516 1.0000 0.0032
-17.250 -0.9386 0.07761 0.07385 -0.0531 1.0000 0.0034
-17.000 -0.9482 0.07298 0.06912 -0.0550 1.0000 0.0032
-16.750 -0.9468 0.06994 0.06602 -0.0562 1.0000 0.0034
-16.500 -0.9543 0.06579 0.06178 -0.0577 1.0000 0.0033
-16.250 -0.9553 0.06259 0.05851 -0.0589 1.0000 0.0034
-16.000 -0.9551 0.05961 0.05546 -0.0598 1.0000 0.0034
-15.750 -0.9559 0.05657 0.05236 -0.0607 1.0000 0.0035
-15.500 -0.9553 0.05379 0.04951 -0.0615 1.0000 0.0035
-15.250 -0.9543 0.05112 0.04677 -0.0621 1.0000 0.0035
-15.000 -0.9511 0.04877 0.04438 -0.0626 1.0000 0.0035
-14.750 -0.9511 0.04616 0.04170 -0.0631 1.0000 0.0035
-14.500 -0.9462 0.04418 0.03967 -0.0633 1.0000 0.0036
-14.250 -0.9442 0.04201 0.03744 -0.0633 1.0000 0.0036
-14.000 -0.9426 0.03987 0.03525 -0.0633 1.0000 0.0036
-13.750 -0.9388 0.03801 0.03334 -0.0631 1.0000 0.0037
-13.500 -0.9396 0.03579 0.03107 -0.0629 1.0000 0.0037
-13.250 -0.9387 0.03381 0.02905 -0.0624 1.0000 0.0038
-13.000 -0.9263 0.03187 0.02706 -0.0639 0.9993 0.0038
-12.750 -0.9047 0.02974 0.02487 -0.0674 0.9968 0.0039
-12.500 -0.8896 0.02789 0.02296 -0.0691 0.9924 0.0041
-12.250 -0.8872 0.02631 0.02136 -0.0678 0.9804 0.0041
-12.000 -0.8515 0.02448 0.01946 -0.0731 0.9472 0.0042
-11.750 -0.7552 0.02255 0.01741 -0.0901 0.9221 0.0046
-11.500 -0.6785 0.02128 0.01579 -0.1027 0.8480 0.0049
-11.250 -0.6720 0.02030 0.01458 -0.1014 0.7995 0.0050
-10.750 -0.6588 0.01827 0.01228 -0.0986 0.7486 0.0052
-10.500 -0.6567 0.01729 0.01118 -0.0965 0.7299 0.0053
-10.250 -0.6492 0.01650 0.01028 -0.0950 0.7133 0.0055
-10.000 -0.6347 0.01592 0.00961 -0.0938 0.6979 0.0058
-9.750 -0.6173 0.01543 0.00905 -0.0928 0.6824 0.0061
-9.500 -0.5978 0.01500 0.00853 -0.0921 0.6690 0.0065
-9.250 -0.5770 0.01461 0.00807 -0.0915 0.6561 0.0069
-9.000 -0.5553 0.01424 0.00763 -0.0910 0.6449 0.0074
-8.750 -0.5327 0.01387 0.00721 -0.0905 0.6344 0.0080
-8.500 -0.5094 0.01353 0.00681 -0.0902 0.6248 0.0090
-8.250 -0.4855 0.01320 0.00644 -0.0899 0.6149 0.0103
-8.000 -0.4611 0.01288 0.00608 -0.0897 0.6061 0.0122
-7.750 -0.4365 0.01256 0.00573 -0.0895 0.5964 0.0155
-7.500 -0.4111 0.01227 0.00542 -0.0894 0.5877 0.0190
-7.250 -0.3856 0.01200 0.00511 -0.0893 0.5781 0.0234
-7.000 -0.3596 0.01170 0.00481 -0.0893 0.5706 0.0293
-6.750 -0.3335 0.01141 0.00452 -0.0893 0.5628 0.0378
-6.500 -0.3072 0.01111 0.00423 -0.0893 0.5561 0.0489
-6.250 -0.2806 0.01080 0.00396 -0.0894 0.5492 0.0625
-5.750 -0.2273 0.01008 0.00338 -0.0897 0.5366 0.1108
-5.500 -0.2015 0.00943 0.00296 -0.0900 0.5301 0.1731
-5.250 -0.1756 0.00871 0.00252 -0.0904 0.5237 0.2502
-5.000 -0.1483 0.00822 0.00225 -0.0908 0.5180 0.3142
-4.750 -0.1199 0.00804 0.00213 -0.0910 0.5118 0.3441
-4.500 -0.0913 0.00795 0.00206 -0.0912 0.5067 0.3665
-4.250 -0.0623 0.00790 0.00200 -0.0915 0.5022 0.3810
-4.000 -0.0333 0.00786 0.00196 -0.0917 0.4973 0.3900
-3.750 -0.0044 0.00786 0.00193 -0.0919 0.4924 0.4005
-3.500 0.0247 0.00788 0.00192 -0.0921 0.4881 0.4125
-3.250 0.0537 0.00785 0.00190 -0.0923 0.4836 0.4188
-3.000 0.0828 0.00786 0.00187 -0.0925 0.4789 0.4216
-2.750 0.1117 0.00789 0.00184 -0.0927 0.4746 0.4240
-2.500 0.1408 0.00790 0.00181 -0.0929 0.4713 0.4264
-2.250 0.1700 0.00792 0.00179 -0.0931 0.4680 0.4284
-2.000 0.1991 0.00792 0.00177 -0.0933 0.4644 0.4308
-1.750 0.2280 0.00794 0.00177 -0.0935 0.4606 0.4331
-1.250 0.2859 0.00799 0.00177 -0.0939 0.4538 0.4382
-1.000 0.3150 0.00800 0.00177 -0.0941 0.4509 0.4408
-0.750 0.3441 0.00803 0.00178 -0.0943 0.4479 0.4431
-0.500 0.3729 0.00808 0.00179 -0.0945 0.4449 0.4449
-0.250 0.4016 0.00812 0.00181 -0.0947 0.4416 0.4470
0.000 0.4304 0.00815 0.00184 -0.0949 0.4387 0.4495
0.250 0.4595 0.00816 0.00186 -0.0951 0.4362 0.4522
0.500 0.4884 0.00819 0.00190 -0.0953 0.4337 0.4550
0.750 0.5172 0.00823 0.00193 -0.0955 0.4309 0.4577
1.000 0.5459 0.00829 0.00197 -0.0956 0.4279 0.4600
1.250 0.5743 0.00835 0.00201 -0.0957 0.4249 0.4620
1.500 0.6029 0.00841 0.00207 -0.0959 0.4223 0.4642
1.750 0.6318 0.00843 0.00211 -0.0961 0.4202 0.4669
2.000 0.6605 0.00847 0.00217 -0.0963 0.4177 0.4696
2.250 0.6891 0.00852 0.00223 -0.0964 0.4150 0.4724
2.500 0.7175 0.00858 0.00230 -0.0966 0.4123 0.4754
2.750 0.7457 0.00865 0.00237 -0.0966 0.4094 0.4781
3.250 0.8023 0.00878 0.00252 -0.0969 0.4044 0.4834
3.500 0.8308 0.00882 0.00261 -0.0970 0.4018 0.4864
3.750 0.8591 0.00888 0.00269 -0.0972 0.3990 0.4895
4.000 0.8870 0.00896 0.00278 -0.0972 0.3958 0.4925
4.250 0.9147 0.00906 0.00288 -0.0972 0.3923 0.4953
4.500 0.9425 0.00915 0.00298 -0.0973 0.3890 0.4982
4.750 0.9707 0.00920 0.00308 -0.0974 0.3854 0.5021
5.000 0.9984 0.00928 0.00319 -0.0975 0.3809 0.5060
5.250 1.0256 0.00939 0.00331 -0.0974 0.3765 0.5097
5.500 1.0529 0.00950 0.00343 -0.0974 0.3726 0.5130
5.750 1.0806 0.00958 0.00355 -0.0974 0.3684 0.5162
6.000 1.1076 0.00968 0.00368 -0.0974 0.3627 0.5203
6.250 1.1342 0.00982 0.00383 -0.0972 0.3568 0.5246
6.500 1.1612 0.00993 0.00397 -0.0972 0.3503 0.5293
7.000 1.2134 0.01024 0.00431 -0.0967 0.3351 0.5387
7.250 1.2384 0.01045 0.00451 -0.0964 0.3257 0.5437
7.500 1.2631 0.01067 0.00472 -0.0959 0.3138 0.5485
7.750 1.2867 0.01095 0.00498 -0.0954 0.2996 0.5532
8.000 1.3092 0.01128 0.00527 -0.0946 0.2842 0.5593
8.250 1.3306 0.01168 0.00561 -0.0937 0.2676 0.5656
8.500 1.3505 0.01213 0.00601 -0.0925 0.2494 0.5716
8.750 1.3691 0.01262 0.00644 -0.0911 0.2292 0.5786
9.000 1.3861 0.01317 0.00691 -0.0895 0.2098 0.5850
9.250 1.4006 0.01380 0.00746 -0.0875 0.1894 0.5915
9.500 1.4129 0.01440 0.00799 -0.0851 0.1708 0.5989
9.750 1.4234 0.01495 0.00850 -0.0823 0.1564 0.6063
10.000 1.4331 0.01556 0.00909 -0.0795 0.1430 0.6157
10.250 1.4422 0.01622 0.00971 -0.0767 0.1305 0.6246
10.500 1.4489 0.01697 0.01044 -0.0737 0.1174 0.6347
10.750 1.4537 0.01783 0.01127 -0.0705 0.1049 0.6444
11.000 1.4587 0.01871 0.01216 -0.0676 0.0955 0.6552
11.250 1.4647 0.01961 0.01309 -0.0650 0.0879 0.6669
11.500 1.4690 0.02066 0.01417 -0.0625 0.0810 0.6797
11.750 1.4716 0.02190 0.01546 -0.0601 0.0746 0.6952
12.000 1.4745 0.02325 0.01686 -0.0580 0.0683 0.7132
12.250 1.4756 0.02482 0.01851 -0.0560 0.0628 0.7347
12.500 1.4775 0.02648 0.02026 -0.0544 0.0581 0.7606
12.750 1.4782 0.02832 0.02221 -0.0529 0.0538 0.7949
13.000 1.4755 0.03008 0.02426 -0.0508 0.0501 0.8903
13.250 1.4760 0.03232 0.02661 -0.0501 0.0457 1.0000
13.500 1.4755 0.03475 0.02908 -0.0494 0.0425 1.0000
13.750 1.4751 0.03726 0.03163 -0.0488 0.0394 1.0000
14.000 1.4728 0.04002 0.03443 -0.0484 0.0364 1.0000
14.250 1.4705 0.04288 0.03733 -0.0480 0.0332 1.0000
14.500 1.4651 0.04614 0.04062 -0.0479 0.0297 1.0000
14.750 1.4631 0.04915 0.04367 -0.0478 0.0275 1.0000
15.000 1.4604 0.05232 0.04689 -0.0479 0.0255 1.0000
15.250 1.4554 0.05586 0.05046 -0.0482 0.0224 1.0000
15.500 1.4554 0.05890 0.05356 -0.0485 0.0213 1.0000
15.750 1.4532 0.06227 0.05698 -0.0490 0.0196 1.0000
16.000 1.4514 0.06570 0.06046 -0.0496 0.0184 1.0000
16.250 1.4498 0.06915 0.06396 -0.0503 0.0168 1.0000
16.500 1.4489 0.07256 0.06742 -0.0510 0.0158 1.0000
16.750 1.4480 0.07606 0.07098 -0.0519 0.0150 1.0000
17.000 1.4468 0.07965 0.07462 -0.0528 0.0137 1.0000
17.250 1.4445 0.08345 0.07847 -0.0539 0.0126 1.0000
17.500 1.4437 0.08709 0.08217 -0.0549 0.0116 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 554 AIRFOIL (e554-il)