EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.96 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e558-il-1000000.txt Download as CSV file: xf-e558-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 558 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8127 0.08666 0.08340 -0.0543 1.0000 0.0090
-16.000 -0.8193 0.08244 0.07913 -0.0561 1.0000 0.0090
-15.750 -0.8241 0.07847 0.07509 -0.0578 1.0000 0.0091
-15.500 -0.8284 0.07450 0.07108 -0.0596 1.0000 0.0092
-15.250 -0.8347 0.07061 0.06713 -0.0611 1.0000 0.0091
-15.000 -0.8410 0.06661 0.06306 -0.0628 1.0000 0.0094
-14.750 -0.8485 0.06278 0.05917 -0.0643 1.0000 0.0092
-14.500 -0.8573 0.05890 0.05523 -0.0657 1.0000 0.0093
-14.250 -0.8678 0.05498 0.05124 -0.0670 1.0000 0.0095
-14.000 -0.8791 0.05122 0.04741 -0.0681 1.0000 0.0094
-13.750 -0.8897 0.04757 0.04370 -0.0691 1.0000 0.0094
-13.500 -0.9013 0.04394 0.04000 -0.0699 1.0000 0.0096
-13.250 -0.9168 0.04011 0.03610 -0.0705 1.0000 0.0095
-13.000 -0.9318 0.03654 0.03247 -0.0708 1.0000 0.0095
-12.750 -0.9484 0.03313 0.02898 -0.0705 1.0000 0.0095
-12.500 -0.9788 0.02963 0.02539 -0.0689 1.0000 0.0095
-12.250 -0.9585 0.02589 0.02150 -0.0765 0.9974 0.0096
-12.000 -0.9264 0.02421 0.01971 -0.0808 0.9949 0.0098
-11.750 -0.8979 0.02219 0.01757 -0.0847 0.9921 0.0100
-11.500 -0.8713 0.02037 0.01565 -0.0875 0.9882 0.0102
-11.250 -0.8397 0.01910 0.01430 -0.0901 0.9858 0.0106
-11.000 -0.8054 0.01814 0.01329 -0.0927 0.9841 0.0108
-10.750 -0.7699 0.01733 0.01243 -0.0953 0.9829 0.0112
-10.500 -0.7455 0.01655 0.01159 -0.0954 0.9774 0.0115
-10.250 -0.7127 0.01583 0.01081 -0.0971 0.9745 0.0118
-10.000 -0.6776 0.01519 0.01012 -0.0991 0.9725 0.0122
-9.750 -0.6514 0.01437 0.00924 -0.0994 0.9669 0.0128
-9.500 -0.6211 0.01370 0.00854 -0.1004 0.9618 0.0135
-9.250 -0.5866 0.01313 0.00793 -0.1021 0.9586 0.0144
-9.000 -0.5638 0.01267 0.00743 -0.1012 0.9477 0.0150
-8.750 -0.5325 0.01202 0.00677 -0.1022 0.9397 0.0169
-8.500 -0.4931 0.01142 0.00615 -0.1048 0.9327 0.0202
-8.250 -0.4463 0.01060 0.00539 -0.1093 0.9247 0.0345
-8.000 -0.3985 0.00984 0.00472 -0.1141 0.9112 0.0572
-7.750 -0.3604 0.00937 0.00426 -0.1165 0.8876 0.0759
-7.500 -0.3310 0.00908 0.00392 -0.1169 0.8620 0.0926
-7.250 -0.3051 0.00885 0.00366 -0.1166 0.8386 0.1078
-7.000 -0.2799 0.00863 0.00342 -0.1161 0.8169 0.1240
-6.750 -0.2547 0.00843 0.00320 -0.1156 0.7968 0.1411
-6.500 -0.2291 0.00827 0.00302 -0.1151 0.7786 0.1571
-6.250 -0.2031 0.00814 0.00286 -0.1147 0.7617 0.1718
-6.000 -0.1769 0.00803 0.00272 -0.1143 0.7456 0.1857
-5.750 -0.1504 0.00793 0.00259 -0.1140 0.7300 0.1999
-5.500 -0.1237 0.00786 0.00249 -0.1137 0.7157 0.2129
-5.250 -0.0970 0.00780 0.00240 -0.1133 0.7015 0.2257
-5.000 -0.0698 0.00773 0.00231 -0.1131 0.6876 0.2374
-4.750 -0.0423 0.00772 0.00223 -0.1129 0.6743 0.2450
-4.500 -0.0151 0.00767 0.00216 -0.1127 0.6619 0.2538
-4.250 0.0124 0.00769 0.00210 -0.1124 0.6492 0.2606
-4.000 0.0400 0.00763 0.00203 -0.1123 0.6369 0.2692
-3.750 0.0676 0.00764 0.00198 -0.1121 0.6253 0.2761
-3.500 0.0950 0.00762 0.00192 -0.1119 0.6137 0.2838
-3.250 0.1231 0.00761 0.00188 -0.1117 0.6031 0.2911
-3.000 0.1506 0.00763 0.00185 -0.1116 0.5921 0.2982
-2.750 0.1784 0.00762 0.00182 -0.1114 0.5811 0.3056
-2.500 0.2064 0.00765 0.00179 -0.1113 0.5713 0.3115
-2.250 0.2340 0.00765 0.00177 -0.1111 0.5612 0.3196
-2.000 0.2621 0.00766 0.00176 -0.1110 0.5515 0.3266
-1.750 0.2895 0.00770 0.00175 -0.1108 0.5413 0.3332
-1.500 0.3177 0.00770 0.00174 -0.1107 0.5323 0.3406
-1.250 0.3453 0.00777 0.00175 -0.1106 0.5233 0.3467
-1.000 0.3734 0.00776 0.00175 -0.1105 0.5149 0.3543
-0.750 0.4009 0.00782 0.00177 -0.1103 0.5058 0.3614
-0.500 0.4290 0.00784 0.00178 -0.1102 0.4976 0.3684
-0.250 0.4563 0.00790 0.00181 -0.1100 0.4890 0.3755
0.000 0.4846 0.00793 0.00183 -0.1100 0.4819 0.3820
0.250 0.5120 0.00798 0.00186 -0.1098 0.4737 0.3900
0.500 0.5399 0.00802 0.00190 -0.1097 0.4665 0.3974
0.750 0.5676 0.00807 0.00194 -0.1095 0.4589 0.4044
1.000 0.5950 0.00813 0.00199 -0.1093 0.4521 0.4126
1.250 0.6230 0.00818 0.00204 -0.1092 0.4456 0.4199
1.500 0.6500 0.00825 0.00210 -0.1090 0.4384 0.4285
1.750 0.6779 0.00830 0.00216 -0.1089 0.4324 0.4366
2.000 0.7053 0.00835 0.00222 -0.1087 0.4257 0.4462
2.250 0.7322 0.00846 0.00230 -0.1085 0.4193 0.4551
2.500 0.7601 0.00848 0.00238 -0.1084 0.4142 0.4656
2.750 0.7872 0.00856 0.00245 -0.1082 0.4081 0.4763
3.000 0.8139 0.00865 0.00256 -0.1079 0.4018 0.4885
3.250 0.8416 0.00869 0.00264 -0.1078 0.3970 0.5009
3.500 0.8686 0.00876 0.00274 -0.1076 0.3916 0.5152
3.750 0.8947 0.00888 0.00286 -0.1072 0.3855 0.5315
4.000 0.9223 0.00891 0.00296 -0.1071 0.3811 0.5496
4.250 0.9491 0.00897 0.00308 -0.1068 0.3759 0.5699
4.500 0.9749 0.00908 0.00322 -0.1064 0.3700 0.5947
4.750 1.0019 0.00912 0.00335 -0.1062 0.3656 0.6226
5.000 1.0284 0.00917 0.00349 -0.1059 0.3605 0.6544
5.500 1.0793 0.00929 0.00382 -0.1050 0.3503 0.7398
5.750 1.1046 0.00928 0.00398 -0.1044 0.3459 0.7965
6.000 1.1258 0.00924 0.00416 -0.1029 0.3410 0.8771
6.250 1.1518 0.00928 0.00430 -0.1024 0.3351 1.0000
6.500 1.1786 0.00939 0.00443 -0.1022 0.3310 1.0000
6.750 1.2043 0.00955 0.00458 -0.1018 0.3254 1.0000
7.000 1.2284 0.00979 0.00478 -0.1011 0.3190 1.0000
7.250 1.2548 0.00991 0.00492 -0.1008 0.3148 1.0000
7.500 1.2798 0.01008 0.00510 -0.1003 0.3091 1.0000
7.750 1.3031 0.01034 0.00532 -0.0995 0.3027 1.0000
8.000 1.3287 0.01047 0.00548 -0.0991 0.2982 1.0000
8.250 1.3526 0.01069 0.00568 -0.0984 0.2918 1.0000
8.500 1.3758 0.01093 0.00591 -0.0976 0.2841 1.0000
8.750 1.3986 0.01117 0.00613 -0.0968 0.2753 1.0000
9.000 1.4208 0.01143 0.00637 -0.0958 0.2669 1.0000
9.250 1.4418 0.01169 0.00662 -0.0946 0.2593 1.0000
9.500 1.4621 0.01197 0.00688 -0.0933 0.2517 1.0000
9.750 1.4808 0.01230 0.00718 -0.0917 0.2422 1.0000
10.000 1.4997 0.01262 0.00749 -0.0902 0.2326 1.0000
10.250 1.5164 0.01304 0.00787 -0.0883 0.2213 1.0000
10.500 1.5319 0.01351 0.00828 -0.0863 0.2091 1.0000
10.750 1.5460 0.01404 0.00875 -0.0842 0.1955 1.0000
11.000 1.5588 0.01464 0.00929 -0.0818 0.1812 1.0000
11.250 1.5701 0.01529 0.00988 -0.0793 0.1673 1.0000
11.500 1.5809 0.01598 0.01052 -0.0768 0.1548 1.0000
11.750 1.5901 0.01675 0.01123 -0.0742 0.1422 1.0000
12.000 1.5981 0.01759 0.01203 -0.0715 0.1304 1.0000
12.250 1.6044 0.01854 0.01295 -0.0688 0.1191 1.0000
12.500 1.6090 0.01962 0.01398 -0.0660 0.1082 1.0000
12.750 1.6124 0.02083 0.01516 -0.0633 0.0983 1.0000
13.000 1.6158 0.02212 0.01643 -0.0608 0.0897 1.0000
13.250 1.6194 0.02349 0.01779 -0.0586 0.0820 1.0000
13.500 1.6211 0.02508 0.01938 -0.0564 0.0750 1.0000
13.750 1.6218 0.02685 0.02115 -0.0545 0.0686 1.0000
14.000 1.6238 0.02864 0.02297 -0.0529 0.0630 1.0000
14.250 1.6216 0.03089 0.02522 -0.0513 0.0573 1.0000
14.500 1.6217 0.03309 0.02745 -0.0501 0.0528 1.0000
14.750 1.6187 0.03567 0.03006 -0.0491 0.0482 1.0000
15.000 1.6150 0.03846 0.03289 -0.0482 0.0441 1.0000
15.250 1.6115 0.04138 0.03585 -0.0477 0.0404 1.0000
15.500 1.6045 0.04476 0.03927 -0.0473 0.0369 1.0000
15.750 1.5991 0.04813 0.04269 -0.0472 0.0335 1.0000
16.000 1.5902 0.05203 0.04665 -0.0472 0.0304 1.0000
16.250 1.5820 0.05598 0.05064 -0.0475 0.0273 1.0000
16.500 1.5709 0.06044 0.05516 -0.0481 0.0240 1.0000
16.750 1.5606 0.06493 0.05972 -0.0489 0.0219 1.0000
17.000 1.5502 0.06957 0.06442 -0.0498 0.0197 1.0000
17.250 1.5404 0.07426 0.06919 -0.0509 0.0183 1.0000
17.500 1.5316 0.07893 0.07393 -0.0521 0.0171 1.0000
17.750 1.5223 0.08374 0.07883 -0.0535 0.0163 1.0000
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