EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 551 AIRFOIL (e551-il) Reynolds number: 500,000 Max Cl/Cd: 102.43 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e551-il-500000.txt Download as CSV file: xf-e551-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 551 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.4109 0.12351 0.12108 -0.0531 1.0000 0.0095
-16.500 -0.5269 0.12720 0.12455 -0.0474 1.0000 0.0093
-16.250 -0.5510 0.11742 0.11472 -0.0518 1.0000 0.0091
-16.000 -0.5770 0.10718 0.10437 -0.0572 1.0000 0.0089
-15.750 -0.5992 0.09845 0.09551 -0.0619 1.0000 0.0088
-15.500 -0.6243 0.08979 0.08669 -0.0666 1.0000 0.0086
-15.250 -0.6498 0.08173 0.07844 -0.0708 1.0000 0.0086
-15.000 -0.6707 0.07506 0.07159 -0.0740 1.0000 0.0084
-14.750 -0.6873 0.06948 0.06584 -0.0764 1.0000 0.0083
-14.500 -0.7079 0.06367 0.05981 -0.0785 1.0000 0.0083
-14.250 -0.7218 0.05909 0.05505 -0.0797 1.0000 0.0081
-14.000 -0.7318 0.05530 0.05109 -0.0805 1.0000 0.0081
-13.750 -0.7426 0.05158 0.04715 -0.0807 1.0000 0.0079
-13.500 -0.7457 0.04895 0.04442 -0.0807 1.0000 0.0081
-13.250 -0.7491 0.04632 0.04165 -0.0803 1.0000 0.0081
-13.000 -0.7504 0.04402 0.03923 -0.0797 1.0000 0.0080
-12.750 -0.7504 0.04196 0.03706 -0.0788 1.0000 0.0080
-12.500 -0.7498 0.04014 0.03517 -0.0778 1.0000 0.0082
-12.250 -0.7492 0.03846 0.03342 -0.0763 1.0000 0.0083
-12.000 -0.7497 0.03697 0.03187 -0.0745 1.0000 0.0083
-11.750 -0.7446 0.03544 0.03027 -0.0738 0.9993 0.0085
-11.500 -0.7183 0.03350 0.02820 -0.0769 0.9958 0.0088
-11.250 -0.6931 0.03172 0.02633 -0.0795 0.9899 0.0090
-11.000 -0.6675 0.03007 0.02457 -0.0822 0.9816 0.0093
-10.750 -0.6512 0.02809 0.02255 -0.0835 0.9669 0.0097
-10.500 -0.6249 0.02630 0.02073 -0.0868 0.9574 0.0101
-10.250 -0.5923 0.02456 0.01893 -0.0912 0.9481 0.0103
-10.000 -0.5502 0.02295 0.01722 -0.0972 0.9411 0.0114
-9.750 -0.5118 0.02099 0.01515 -0.1034 0.9270 0.0121
-9.500 -0.4826 0.01938 0.01342 -0.1074 0.9075 0.0128
-9.250 -0.4691 0.01824 0.01215 -0.1074 0.8862 0.0137
-9.000 -0.4666 0.01732 0.01107 -0.1051 0.8669 0.0148
-8.750 -0.4599 0.01657 0.01022 -0.1028 0.8522 0.0156
-8.500 -0.4455 0.01603 0.00958 -0.1013 0.8404 0.0179
-8.250 -0.4319 0.01540 0.00889 -0.0997 0.8287 0.0204
-8.000 -0.4162 0.01480 0.00824 -0.0984 0.8184 0.0255
-7.750 -0.4000 0.01413 0.00755 -0.0971 0.8090 0.0338
-7.500 -0.3822 0.01351 0.00697 -0.0961 0.7995 0.0476
-7.250 -0.3631 0.01289 0.00640 -0.0952 0.7911 0.0699
-7.000 -0.3436 0.01224 0.00588 -0.0945 0.7822 0.1007
-6.750 -0.3237 0.01153 0.00532 -0.0939 0.7744 0.1478
-6.500 -0.3061 0.01046 0.00461 -0.0932 0.7660 0.2308
-6.250 -0.2883 0.00933 0.00402 -0.0926 0.7588 0.3678
-6.000 -0.2617 0.00925 0.00399 -0.0925 0.7511 0.4103
-5.750 -0.2339 0.00930 0.00395 -0.0925 0.7438 0.4292
-5.500 -0.2059 0.00938 0.00395 -0.0925 0.7365 0.4426
-5.250 -0.1781 0.00943 0.00395 -0.0925 0.7293 0.4516
-5.000 -0.1497 0.00955 0.00392 -0.0926 0.7228 0.4600
-4.750 -0.1218 0.00957 0.00394 -0.0926 0.7157 0.4669
-4.500 -0.0935 0.00968 0.00393 -0.0926 0.7094 0.4738
-4.250 -0.0656 0.00970 0.00390 -0.0927 0.7024 0.4796
-4.000 -0.0375 0.00987 0.00405 -0.0926 0.6957 0.4883
-3.750 -0.0095 0.01000 0.00409 -0.0926 0.6895 0.4961
-3.500 0.0187 0.00997 0.00406 -0.0927 0.6830 0.4993
-3.250 0.0470 0.00997 0.00397 -0.0928 0.6771 0.5017
-3.000 0.0753 0.00995 0.00389 -0.0930 0.6710 0.5040
-2.750 0.1036 0.00992 0.00379 -0.0931 0.6646 0.5062
-2.500 0.1320 0.00995 0.00370 -0.0934 0.6590 0.5084
-2.250 0.1603 0.00991 0.00363 -0.0935 0.6530 0.5104
-2.000 0.1884 0.00983 0.00351 -0.0937 0.6474 0.5126
-1.750 0.2168 0.00983 0.00346 -0.0939 0.6421 0.5145
-1.500 0.2449 0.00980 0.00343 -0.0940 0.6364 0.5166
-1.250 0.2730 0.00980 0.00339 -0.0941 0.6308 0.5188
-1.000 0.3015 0.00985 0.00337 -0.0943 0.6258 0.5213
-0.750 0.3297 0.00984 0.00336 -0.0945 0.6206 0.5238
-0.500 0.3580 0.00987 0.00333 -0.0947 0.6154 0.5260
-0.250 0.3863 0.00989 0.00329 -0.0949 0.6106 0.5281
0.000 0.4142 0.00986 0.00329 -0.0950 0.6056 0.5304
0.250 0.4423 0.00986 0.00330 -0.0951 0.6006 0.5328
0.500 0.4705 0.00991 0.00332 -0.0953 0.5961 0.5352
0.750 0.4987 0.00997 0.00336 -0.0955 0.5916 0.5380
1.000 0.5266 0.00999 0.00339 -0.0956 0.5868 0.5409
1.250 0.5548 0.01005 0.00342 -0.0958 0.5822 0.5435
1.500 0.5829 0.01009 0.00344 -0.0960 0.5779 0.5463
1.750 0.6106 0.01010 0.00350 -0.0960 0.5735 0.5491
2.000 0.6383 0.01013 0.00356 -0.0961 0.5689 0.5520
2.250 0.6661 0.01020 0.00362 -0.0962 0.5646 0.5551
2.500 0.6944 0.01031 0.00370 -0.0965 0.5603 0.5583
2.750 0.7217 0.01035 0.00377 -0.0965 0.5559 0.5615
3.000 0.7489 0.01036 0.00384 -0.0965 0.5512 0.5651
3.250 0.7765 0.01044 0.00392 -0.0965 0.5468 0.5688
3.500 0.8038 0.01053 0.00404 -0.0966 0.5422 0.5727
3.750 0.8308 0.01058 0.00413 -0.0965 0.5372 0.5766
4.000 0.8577 0.01063 0.00420 -0.0965 0.5323 0.5804
4.250 0.8848 0.01074 0.00433 -0.0965 0.5275 0.5846
4.500 0.9110 0.01077 0.00445 -0.0963 0.5224 0.5891
4.750 0.9376 0.01085 0.00454 -0.0962 0.5174 0.5939
5.000 0.9645 0.01098 0.00468 -0.0962 0.5124 0.5987
5.250 0.9899 0.01101 0.00482 -0.0958 0.5071 0.6042
5.500 1.0156 0.01109 0.00494 -0.0955 0.5014 0.6102
5.750 1.0414 0.01122 0.00508 -0.0953 0.4957 0.6159
6.000 1.0662 0.01126 0.00524 -0.0948 0.4896 0.6222
6.500 1.1155 0.01146 0.00555 -0.0939 0.4771 0.6358
6.750 1.1395 0.01155 0.00571 -0.0933 0.4698 0.6439
7.000 1.1627 0.01169 0.00589 -0.0926 0.4628 0.6519
7.250 1.1859 0.01178 0.00608 -0.0919 0.4546 0.6615
7.500 1.2077 0.01192 0.00628 -0.0909 0.4468 0.6713
7.750 1.2294 0.01204 0.00648 -0.0899 0.4371 0.6822
8.000 1.2497 0.01220 0.00672 -0.0887 0.4272 0.6944
8.250 1.2676 0.01239 0.00696 -0.0870 0.4158 0.7073
8.500 1.2829 0.01258 0.00721 -0.0848 0.4022 0.7217
8.750 1.2963 0.01283 0.00752 -0.0823 0.3873 0.7383
9.000 1.3072 0.01318 0.00790 -0.0794 0.3702 0.7582
9.250 1.3166 0.01360 0.00836 -0.0764 0.3506 0.7824
9.500 1.3217 0.01412 0.00892 -0.0727 0.3284 0.8156
9.750 1.3207 0.01465 0.00956 -0.0679 0.3085 0.8814
10.000 1.3273 0.01538 0.01030 -0.0651 0.2851 1.0000
10.250 1.3305 0.01639 0.01122 -0.0620 0.2641 1.0000
10.500 1.3331 0.01751 0.01225 -0.0591 0.2453 1.0000
10.750 1.3361 0.01871 0.01338 -0.0564 0.2261 1.0000
11.000 1.3378 0.02005 0.01465 -0.0537 0.2078 1.0000
11.250 1.3395 0.02150 0.01603 -0.0513 0.1910 1.0000
11.500 1.3413 0.02304 0.01752 -0.0491 0.1759 1.0000
11.750 1.3421 0.02473 0.01915 -0.0471 0.1607 1.0000
12.000 1.3431 0.02649 0.02087 -0.0452 0.1470 1.0000
12.250 1.3438 0.02837 0.02271 -0.0435 0.1342 1.0000
12.500 1.3448 0.03030 0.02462 -0.0420 0.1231 1.0000
12.750 1.3450 0.03237 0.02667 -0.0407 0.1125 1.0000
13.000 1.3448 0.03456 0.02883 -0.0394 0.1025 1.0000
13.250 1.3469 0.03664 0.03092 -0.0384 0.0937 1.0000
13.500 1.3474 0.03894 0.03321 -0.0375 0.0852 1.0000
13.750 1.3464 0.04145 0.03571 -0.0367 0.0773 1.0000
14.000 1.3479 0.04381 0.03809 -0.0361 0.0704 1.0000
14.250 1.3485 0.04633 0.04062 -0.0356 0.0639 1.0000
14.500 1.3470 0.04915 0.04343 -0.0351 0.0580 1.0000
14.750 1.3491 0.05166 0.04597 -0.0349 0.0527 1.0000
15.000 1.3480 0.05458 0.04891 -0.0347 0.0481 1.0000
15.250 1.3490 0.05734 0.05170 -0.0347 0.0439 1.0000
15.500 1.3484 0.06037 0.05476 -0.0348 0.0403 1.0000
15.750 1.3487 0.06334 0.05776 -0.0349 0.0367 1.0000
16.000 1.3480 0.06651 0.06098 -0.0352 0.0339 1.0000
16.250 1.3481 0.06965 0.06417 -0.0356 0.0313 1.0000
16.500 1.3462 0.07311 0.06766 -0.0361 0.0290 1.0000
16.750 1.3469 0.07630 0.07093 -0.0367 0.0270 1.0000
17.000 1.3438 0.08005 0.07472 -0.0375 0.0252 1.0000
17.250 1.3433 0.08352 0.07827 -0.0382 0.0236 1.0000
17.500 1.3424 0.08711 0.08193 -0.0392 0.0219 1.0000
17.750 1.3370 0.09142 0.08629 -0.0404 0.0205 1.0000
18.000 1.3372 0.09496 0.08994 -0.0414 0.0192 1.0000
18.250 1.3348 0.09893 0.09397 -0.0427 0.0181 1.0000
18.500 1.3278 0.10369 0.09878 -0.0444 0.0170 1.0000
18.750 1.3270 0.10756 0.10276 -0.0458 0.0160 1.0000
19.000 1.3254 0.11155 0.10683 -0.0474 0.0150 1.0000
19.250 1.3188 0.11641 0.11175 -0.0494 0.0143 1.0000
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Polar data table (+)
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