EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 500,000 Max Cl/Cd: 93.74 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e553-il-500000-n5.txt Download as CSV file: xf-e553-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 553 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.6685 0.13747 0.13430 -0.0389 1.0000 0.0044
-18.500 -0.6874 0.12921 0.12591 -0.0429 1.0000 0.0044
-18.250 -0.7051 0.12153 0.11811 -0.0466 1.0000 0.0044
-18.000 -0.7203 0.11464 0.11109 -0.0499 1.0000 0.0044
-17.750 -0.7331 0.10831 0.10465 -0.0529 1.0000 0.0044
-17.500 -0.7447 0.10244 0.09867 -0.0556 1.0000 0.0044
-17.250 -0.7558 0.09678 0.09290 -0.0583 1.0000 0.0045
-17.000 -0.7640 0.09184 0.08785 -0.0605 1.0000 0.0044
-16.750 -0.7725 0.08696 0.08287 -0.0626 1.0000 0.0044
-16.500 -0.7795 0.08248 0.07829 -0.0645 1.0000 0.0044
-16.250 -0.7838 0.07847 0.07419 -0.0661 1.0000 0.0045
-16.000 -0.7888 0.07452 0.07016 -0.0676 1.0000 0.0045
-15.750 -0.7928 0.07084 0.06639 -0.0689 1.0000 0.0045
-15.500 -0.7957 0.06739 0.06285 -0.0700 1.0000 0.0046
-15.250 -0.7984 0.06406 0.05945 -0.0710 1.0000 0.0047
-15.000 -0.7998 0.06103 0.05634 -0.0718 1.0000 0.0047
-14.750 -0.8011 0.05809 0.05331 -0.0724 1.0000 0.0048
-14.500 -0.8012 0.05539 0.05055 -0.0729 1.0000 0.0047
-14.250 -0.8009 0.05283 0.04791 -0.0733 1.0000 0.0049
-14.000 -0.8003 0.05042 0.04544 -0.0735 1.0000 0.0049
-13.750 -0.8002 0.04807 0.04301 -0.0735 1.0000 0.0051
-13.500 -0.8012 0.04579 0.04067 -0.0733 1.0000 0.0051
-13.250 -0.8012 0.04372 0.03855 -0.0729 1.0000 0.0051
-13.000 -0.8009 0.04180 0.03657 -0.0723 1.0000 0.0052
-12.750 -0.8007 0.03996 0.03468 -0.0715 1.0000 0.0053
-12.250 -0.7791 0.03532 0.02991 -0.0754 0.9957 0.0055
-12.000 -0.7641 0.03310 0.02764 -0.0778 0.9891 0.0057
-11.750 -0.7528 0.03122 0.02571 -0.0789 0.9752 0.0057
-11.500 -0.7358 0.02942 0.02385 -0.0808 0.9610 0.0060
-11.250 -0.7099 0.02763 0.02199 -0.0844 0.9506 0.0064
-11.000 -0.6767 0.02580 0.02007 -0.0894 0.9417 0.0065
-10.750 -0.6365 0.02400 0.01816 -0.0957 0.9322 0.0070
-10.500 -0.5933 0.02230 0.01636 -0.1025 0.9203 0.0075
-10.250 -0.5563 0.02080 0.01475 -0.1077 0.9030 0.0080
-10.000 -0.5324 0.01959 0.01340 -0.1100 0.8826 0.0088
-9.500 -0.5164 0.01755 0.01109 -0.1081 0.8450 0.0102
-9.250 -0.5035 0.01689 0.01033 -0.1069 0.8312 0.0113
-9.000 -0.4883 0.01631 0.00967 -0.1058 0.8188 0.0128
-8.750 -0.4711 0.01579 0.00907 -0.1048 0.8079 0.0147
-8.250 -0.4332 0.01481 0.00798 -0.1033 0.7876 0.0211
-8.000 -0.4124 0.01437 0.00750 -0.1027 0.7782 0.0256
-7.750 -0.3909 0.01394 0.00704 -0.1022 0.7690 0.0318
-7.500 -0.3686 0.01352 0.00660 -0.1017 0.7605 0.0397
-7.250 -0.3463 0.01307 0.00616 -0.1013 0.7515 0.0514
-7.000 -0.3233 0.01262 0.00573 -0.1010 0.7435 0.0678
-6.750 -0.3004 0.01211 0.00529 -0.1008 0.7350 0.0924
-6.500 -0.2775 0.01151 0.00481 -0.1006 0.7273 0.1300
-6.250 -0.2554 0.01072 0.00424 -0.1005 0.7191 0.1896
-6.000 -0.2336 0.00973 0.00362 -0.1005 0.7117 0.2833
-5.750 -0.2079 0.00934 0.00339 -0.1006 0.7039 0.3381
-5.500 -0.1805 0.00923 0.00326 -0.1006 0.6969 0.3623
-5.250 -0.1527 0.00916 0.00318 -0.1007 0.6891 0.3800
-5.000 -0.1248 0.00914 0.00310 -0.1008 0.6821 0.3949
-4.750 -0.0965 0.00912 0.00303 -0.1009 0.6749 0.4052
-4.500 -0.0686 0.00913 0.00299 -0.1009 0.6678 0.4148
-4.250 -0.0402 0.00916 0.00299 -0.1011 0.6607 0.4271
-4.000 -0.0120 0.00920 0.00296 -0.1011 0.6536 0.4347
-3.750 0.0164 0.00920 0.00287 -0.1013 0.6472 0.4376
-3.500 0.0446 0.00918 0.00278 -0.1014 0.6401 0.4399
-3.250 0.0725 0.00917 0.00272 -0.1014 0.6334 0.4422
-3.000 0.1009 0.00916 0.00268 -0.1015 0.6264 0.4449
-2.750 0.1289 0.00918 0.00263 -0.1016 0.6200 0.4475
-2.500 0.1573 0.00918 0.00258 -0.1017 0.6137 0.4500
-2.250 0.1854 0.00920 0.00253 -0.1018 0.6066 0.4524
-2.000 0.2136 0.00923 0.00249 -0.1019 0.6005 0.4547
-1.750 0.2418 0.00922 0.00247 -0.1020 0.5940 0.4572
-1.500 0.2695 0.00924 0.00246 -0.1020 0.5876 0.4597
-1.250 0.2977 0.00926 0.00245 -0.1022 0.5813 0.4622
-1.000 0.3257 0.00929 0.00244 -0.1022 0.5748 0.4647
-0.750 0.3536 0.00933 0.00244 -0.1023 0.5691 0.4672
-0.500 0.3818 0.00936 0.00244 -0.1024 0.5626 0.4697
-0.250 0.4094 0.00941 0.00245 -0.1024 0.5564 0.4722
0.000 0.4374 0.00944 0.00248 -0.1025 0.5509 0.4748
0.250 0.4652 0.00947 0.00251 -0.1025 0.5447 0.4774
0.500 0.4925 0.00954 0.00254 -0.1025 0.5388 0.4800
0.750 0.5206 0.00958 0.00258 -0.1026 0.5331 0.4827
1.000 0.5483 0.00964 0.00262 -0.1026 0.5275 0.4853
1.250 0.5755 0.00973 0.00267 -0.1026 0.5221 0.4879
1.500 0.6034 0.00976 0.00273 -0.1026 0.5163 0.4907
1.750 0.6306 0.00982 0.00280 -0.1026 0.5105 0.4937
2.000 0.6577 0.00991 0.00287 -0.1025 0.5055 0.4967
2.250 0.6854 0.00997 0.00295 -0.1026 0.5000 0.4997
2.500 0.7124 0.01006 0.00303 -0.1025 0.4943 0.5026
2.750 0.7392 0.01015 0.00312 -0.1024 0.4891 0.5053
3.000 0.7665 0.01021 0.00322 -0.1024 0.4834 0.5085
3.250 0.7929 0.01031 0.00333 -0.1022 0.4775 0.5121
3.500 0.8196 0.01041 0.00345 -0.1020 0.4719 0.5158
3.750 0.8463 0.01051 0.00356 -0.1019 0.4657 0.5192
4.000 0.8720 0.01063 0.00368 -0.1016 0.4598 0.5223
4.250 0.8986 0.01072 0.00382 -0.1015 0.4543 0.5258
4.500 0.9247 0.01083 0.00396 -0.1013 0.4483 0.5297
4.750 0.9499 0.01098 0.00411 -0.1009 0.4425 0.5340
5.000 0.9760 0.01109 0.00426 -0.1007 0.4358 0.5381
5.250 1.0005 0.01124 0.00443 -0.1002 0.4286 0.5424
5.500 1.0258 0.01137 0.00460 -0.0998 0.4217 0.5470
5.750 1.0502 0.01153 0.00479 -0.0993 0.4144 0.5515
6.000 1.0745 0.01169 0.00498 -0.0988 0.4076 0.5559
6.250 1.0981 0.01186 0.00518 -0.0981 0.3991 0.5609
6.500 1.1214 0.01204 0.00540 -0.0974 0.3907 0.5668
6.750 1.1434 0.01226 0.00562 -0.0965 0.3814 0.5723
7.000 1.1661 0.01244 0.00586 -0.0957 0.3722 0.5784
7.250 1.1863 0.01269 0.00612 -0.0945 0.3624 0.5847
7.500 1.2055 0.01292 0.00638 -0.0930 0.3516 0.5907
7.750 1.2238 0.01317 0.00666 -0.0914 0.3405 0.5974
8.250 1.2562 0.01388 0.00737 -0.0877 0.3140 0.6124
8.750 1.2840 0.01481 0.00828 -0.0833 0.2819 0.6297
9.000 1.2949 0.01541 0.00884 -0.0808 0.2631 0.6388
9.250 1.3044 0.01608 0.00949 -0.0782 0.2452 0.6486
9.500 1.3118 0.01687 0.01023 -0.0754 0.2268 0.6587
10.000 1.3250 0.01864 0.01195 -0.0700 0.1907 0.6834
10.250 1.3303 0.01965 0.01296 -0.0673 0.1744 0.6982
10.500 1.3362 0.02069 0.01402 -0.0649 0.1608 0.7153
11.000 1.3457 0.02304 0.01644 -0.0603 0.1353 0.7588
11.250 1.3486 0.02438 0.01785 -0.0581 0.1231 0.7899
11.500 1.3490 0.02573 0.01933 -0.0554 0.1123 0.8454
11.750 1.3537 0.02708 0.02082 -0.0538 0.1020 1.0000
12.000 1.3580 0.02872 0.02245 -0.0524 0.0929 1.0000
12.250 1.3616 0.03049 0.02422 -0.0510 0.0853 1.0000
12.500 1.3645 0.03238 0.02611 -0.0498 0.0773 1.0000
12.750 1.3685 0.03426 0.02800 -0.0487 0.0709 1.0000
13.250 1.3741 0.03841 0.03219 -0.0469 0.0595 1.0000
13.500 1.3754 0.04075 0.03454 -0.0462 0.0543 1.0000
13.750 1.3783 0.04301 0.03683 -0.0456 0.0499 1.0000
14.000 1.3789 0.04556 0.03940 -0.0451 0.0456 1.0000
14.250 1.3817 0.04798 0.04187 -0.0448 0.0420 1.0000
14.500 1.3816 0.05077 0.04469 -0.0445 0.0385 1.0000
14.750 1.3839 0.05338 0.04736 -0.0444 0.0355 1.0000
15.000 1.3837 0.05634 0.05035 -0.0444 0.0325 1.0000
15.250 1.3851 0.05918 0.05325 -0.0446 0.0302 1.0000
15.500 1.3855 0.06221 0.05634 -0.0448 0.0278 1.0000
15.750 1.3854 0.06536 0.05954 -0.0451 0.0259 1.0000
16.000 1.3863 0.06848 0.06272 -0.0455 0.0240 1.0000
16.250 1.3851 0.07191 0.06620 -0.0461 0.0222 1.0000
16.500 1.3850 0.07528 0.06964 -0.0468 0.0210 1.0000
16.750 1.3846 0.07872 0.07315 -0.0475 0.0191 1.0000
17.000 1.3834 0.08235 0.07685 -0.0484 0.0181 1.0000
17.250 1.3819 0.08609 0.08066 -0.0494 0.0169 1.0000
17.500 1.3812 0.08977 0.08441 -0.0504 0.0157 1.0000
17.750 1.3793 0.09365 0.08836 -0.0516 0.0148 1.0000
18.000 1.3769 0.09768 0.09246 -0.0529 0.0138 1.0000
18.250 1.3758 0.10156 0.09642 -0.0543 0.0129 1.0000
18.500 1.3742 0.10556 0.10050 -0.0557 0.0122 1.0000
18.750 1.3707 0.10990 0.10491 -0.0574 0.0115 1.0000
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