EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 100,000 Max Cl/Cd: 52.88 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e559-il-100000-n5.txt Download as CSV file: xf-e559-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 559 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5509 0.08782 0.08198 -0.0626 1.0000 0.0362
-13.000 -0.5687 0.08161 0.07568 -0.0655 1.0000 0.0365
-12.750 -0.5832 0.07643 0.07043 -0.0677 1.0000 0.0368
-12.500 -0.5953 0.07194 0.06588 -0.0694 1.0000 0.0374
-12.250 -0.6074 0.06766 0.06154 -0.0709 1.0000 0.0380
-12.000 -0.6178 0.06388 0.05769 -0.0719 1.0000 0.0384
-11.750 -0.6298 0.06011 0.05385 -0.0728 1.0000 0.0391
-11.500 -0.6406 0.05677 0.05044 -0.0732 1.0000 0.0397
-11.250 -0.6524 0.05361 0.04722 -0.0732 1.0000 0.0404
-11.000 -0.6648 0.05075 0.04429 -0.0727 1.0000 0.0409
-10.750 -0.6797 0.04813 0.04161 -0.0715 1.0000 0.0414
-10.500 -0.6996 0.04577 0.03926 -0.0695 1.0000 0.0416
-10.250 -0.7184 0.04337 0.03686 -0.0680 1.0000 0.0418
-10.000 -0.7293 0.04072 0.03419 -0.0681 1.0000 0.0424
-9.750 -0.7130 0.03817 0.03158 -0.0719 0.9956 0.0440
-9.500 -0.6840 0.03579 0.02902 -0.0767 0.9882 0.0467
-9.250 -0.6540 0.03352 0.02662 -0.0812 0.9809 0.0503
-9.000 -0.6242 0.03151 0.02448 -0.0851 0.9729 0.0554
-8.750 -0.5965 0.02953 0.02245 -0.0883 0.9640 0.0613
-8.500 -0.5656 0.02774 0.02057 -0.0915 0.9562 0.0702
-8.250 -0.5341 0.02614 0.01892 -0.0944 0.9480 0.0837
-8.000 -0.5036 0.02488 0.01758 -0.0965 0.9392 0.0998
-7.750 -0.4674 0.02377 0.01646 -0.0995 0.9327 0.1176
-7.500 -0.4368 0.02297 0.01560 -0.1009 0.9232 0.1344
-7.250 -0.3986 0.02226 0.01480 -0.1036 0.9172 0.1560
-7.000 -0.3677 0.02180 0.01434 -0.1048 0.9072 0.1755
-6.750 -0.3289 0.02136 0.01382 -0.1072 0.9014 0.1935
-6.500 -0.2977 0.02097 0.01332 -0.1080 0.8911 0.2063
-6.250 -0.2575 0.02051 0.01272 -0.1104 0.8850 0.2199
-6.000 -0.2254 0.02022 0.01231 -0.1112 0.8741 0.2314
-5.750 -0.1849 0.01989 0.01191 -0.1136 0.8670 0.2432
-5.500 -0.1506 0.01958 0.01148 -0.1148 0.8559 0.2541
-5.250 -0.1139 0.01927 0.01099 -0.1164 0.8458 0.2657
-5.000 -0.0755 0.01902 0.01069 -0.1183 0.8362 0.2752
-4.750 -0.0417 0.01876 0.01028 -0.1193 0.8238 0.2851
-4.500 -0.0062 0.01855 0.00998 -0.1206 0.8122 0.2948
-4.000 0.0625 0.01817 0.00932 -0.1228 0.7877 0.3137
-3.750 0.0940 0.01803 0.00912 -0.1234 0.7746 0.3215
-3.500 0.1265 0.01790 0.00881 -0.1241 0.7621 0.3313
-3.250 0.1590 0.01778 0.00863 -0.1248 0.7504 0.3389
-3.000 0.1883 0.01770 0.00841 -0.1250 0.7370 0.3481
-2.750 0.2172 0.01763 0.00829 -0.1250 0.7245 0.3555
-2.500 0.2472 0.01756 0.00809 -0.1253 0.7128 0.3645
-2.250 0.2764 0.01751 0.00797 -0.1254 0.7011 0.3721
-2.000 0.3041 0.01749 0.00786 -0.1253 0.6889 0.3810
-1.750 0.3324 0.01746 0.00777 -0.1252 0.6778 0.3887
-1.500 0.3610 0.01745 0.00765 -0.1252 0.6672 0.3977
-1.250 0.3879 0.01745 0.00762 -0.1249 0.6557 0.4058
-1.000 0.4159 0.01746 0.00755 -0.1248 0.6456 0.4148
-0.750 0.4432 0.01747 0.00752 -0.1246 0.6352 0.4233
-0.500 0.4702 0.01751 0.00751 -0.1243 0.6250 0.4327
-0.250 0.4980 0.01754 0.00748 -0.1242 0.6159 0.4415
0.000 0.5243 0.01760 0.00752 -0.1238 0.6056 0.4516
0.250 0.5516 0.01765 0.00754 -0.1236 0.5971 0.4607
0.500 0.5778 0.01773 0.00760 -0.1232 0.5873 0.4714
0.750 0.6046 0.01780 0.00766 -0.1229 0.5791 0.4814
1.000 0.6307 0.01788 0.00776 -0.1225 0.5701 0.4922
1.250 0.6577 0.01799 0.00782 -0.1222 0.5621 0.5044
1.500 0.6833 0.01808 0.00797 -0.1217 0.5535 0.5159
1.750 0.7100 0.01819 0.00807 -0.1214 0.5462 0.5288
2.000 0.7354 0.01832 0.00824 -0.1209 0.5379 0.5426
2.250 0.7624 0.01845 0.00834 -0.1206 0.5312 0.5581
2.500 0.7873 0.01859 0.00858 -0.1201 0.5230 0.5745
2.750 0.8137 0.01872 0.00873 -0.1197 0.5164 0.5925
3.000 0.8385 0.01888 0.00898 -0.1191 0.5090 0.6129
3.250 0.8636 0.01902 0.00920 -0.1185 0.5021 0.6368
3.500 0.8887 0.01916 0.00941 -0.1178 0.4959 0.6643
4.000 0.9346 0.01940 0.00992 -0.1156 0.4832 0.7397
4.500 0.9714 0.01943 0.01034 -0.1112 0.4708 0.9056
4.750 1.0011 0.01966 0.01049 -0.1116 0.4654 1.0000
5.000 1.0258 0.02004 0.01089 -0.1113 0.4588 1.0000
5.250 1.0517 0.02038 0.01120 -0.1111 0.4528 1.0000
5.500 1.0787 0.02073 0.01149 -0.1110 0.4476 1.0000
5.750 1.1020 0.02114 0.01197 -0.1104 0.4412 1.0000
6.000 1.1274 0.02151 0.01232 -0.1101 0.4356 1.0000
6.250 1.1530 0.02189 0.01268 -0.1098 0.4304 1.0000
6.500 1.1752 0.02234 0.01321 -0.1090 0.4241 1.0000
6.750 1.1999 0.02273 0.01359 -0.1086 0.4187 1.0000
7.000 1.2241 0.02315 0.01403 -0.1081 0.4135 1.0000
7.250 1.2450 0.02363 0.01461 -0.1071 0.4072 1.0000
7.500 1.2689 0.02403 0.01501 -0.1065 0.4019 1.0000
7.750 1.2910 0.02450 0.01554 -0.1057 0.3964 1.0000
8.000 1.3106 0.02501 0.01616 -0.1045 0.3901 1.0000
8.250 1.3338 0.02542 0.01656 -0.1038 0.3848 1.0000
8.500 1.3527 0.02596 0.01721 -0.1025 0.3790 1.0000
8.750 1.3708 0.02648 0.01784 -0.1011 0.3727 1.0000
9.000 1.3938 0.02689 0.01822 -0.1004 0.3675 1.0000
9.250 1.4072 0.02754 0.01904 -0.0984 0.3609 1.0000
9.500 1.4241 0.02805 0.01964 -0.0968 0.3547 1.0000
9.750 1.4418 0.02854 0.02016 -0.0953 0.3491 1.0000
10.000 1.4502 0.02924 0.02102 -0.0925 0.3422 1.0000
10.250 1.4660 0.02972 0.02152 -0.0908 0.3362 1.0000
10.500 1.4736 0.03051 0.02245 -0.0880 0.3295 1.0000
10.750 1.4831 0.03120 0.02325 -0.0856 0.3227 1.0000
11.000 1.4930 0.03194 0.02405 -0.0833 0.3162 1.0000
11.250 1.4971 0.03294 0.02520 -0.0806 0.3089 1.0000
11.500 1.5074 0.03369 0.02597 -0.0786 0.3024 1.0000
11.750 1.5067 0.03507 0.02754 -0.0757 0.2947 1.0000
12.000 1.5148 0.03599 0.02847 -0.0738 0.2879 1.0000
12.250 1.5112 0.03778 0.03048 -0.0712 0.2799 1.0000
12.500 1.5158 0.03906 0.03177 -0.0694 0.2727 1.0000
12.750 1.5103 0.04128 0.03419 -0.0673 0.2646 1.0000
13.000 1.5124 0.04294 0.03584 -0.0658 0.2571 1.0000
13.250 1.5042 0.04575 0.03886 -0.0643 0.2487 1.0000
13.500 1.5023 0.04803 0.04117 -0.0632 0.2409 1.0000
13.750 1.4927 0.05135 0.04465 -0.0624 0.2323 1.0000
14.000 1.4868 0.05440 0.04776 -0.0618 0.2243 1.0000
14.250 1.4768 0.05813 0.05160 -0.0616 0.2158 1.0000
14.500 1.4671 0.06201 0.05559 -0.0616 0.2077 1.0000
14.750 1.4580 0.06597 0.05959 -0.0619 0.1993 1.0000
15.000 1.4454 0.07068 0.06443 -0.0626 0.1912 1.0000
15.250 1.4382 0.07464 0.06837 -0.0631 0.1831 1.0000
15.500 1.4234 0.08007 0.07395 -0.0644 0.1749 1.0000
15.750 1.4156 0.08443 0.07831 -0.0654 0.1672 1.0000
16.000 1.4032 0.08974 0.08373 -0.0669 0.1594 1.0000
16.250 1.3951 0.09442 0.08843 -0.0682 0.1520 1.0000
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Polar data table (+)
Polar graphs
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