EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 100,000 Max Cl/Cd: 54.91 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e557-il-100000-n5.txt Download as CSV file: xf-e557-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5030 0.09574 0.09026 -0.0618 1.0000 0.0217
-12.750 -0.5320 0.08661 0.08102 -0.0665 1.0000 0.0209
-12.500 -0.5610 0.07876 0.07302 -0.0706 1.0000 0.0207
-12.250 -0.5870 0.07224 0.06634 -0.0736 1.0000 0.0203
-12.000 -0.6056 0.06750 0.06146 -0.0753 1.0000 0.0204
-11.750 -0.6233 0.06315 0.05696 -0.0762 1.0000 0.0203
-11.500 -0.6382 0.05961 0.05331 -0.0765 1.0000 0.0206
-11.250 -0.6524 0.05654 0.05011 -0.0762 1.0000 0.0209
-11.000 -0.6655 0.05379 0.04725 -0.0752 1.0000 0.0210
-10.750 -0.6812 0.05131 0.04465 -0.0736 1.0000 0.0214
-10.500 -0.6975 0.04928 0.04249 -0.0713 1.0000 0.0218
-10.250 -0.7143 0.04758 0.04072 -0.0682 1.0000 0.0219
-10.000 -0.7326 0.04590 0.03891 -0.0651 1.0000 0.0222
-9.750 -0.7182 0.04350 0.03637 -0.0676 0.9958 0.0231
-9.500 -0.6944 0.04134 0.03409 -0.0707 0.9902 0.0243
-9.250 -0.6694 0.03919 0.03174 -0.0729 0.9849 0.0256
-9.000 -0.6456 0.03733 0.02963 -0.0740 0.9790 0.0270
-8.750 -0.6191 0.03570 0.02802 -0.0765 0.9734 0.0289
-8.500 -0.5955 0.03422 0.02634 -0.0776 0.9662 0.0321
-8.250 -0.5671 0.03269 0.02486 -0.0801 0.9611 0.0350
-8.000 -0.5448 0.03136 0.02343 -0.0807 0.9530 0.0387
-7.750 -0.5140 0.02996 0.02200 -0.0834 0.9480 0.0441
-7.500 -0.4911 0.02867 0.02071 -0.0845 0.9397 0.0498
-7.250 -0.4592 0.02729 0.01930 -0.0873 0.9346 0.0587
-7.000 -0.4327 0.02602 0.01800 -0.0890 0.9271 0.0697
-6.750 -0.4001 0.02465 0.01662 -0.0919 0.9214 0.0872
-6.500 -0.3620 0.02299 0.01506 -0.0963 0.9179 0.1171
-6.250 -0.3341 0.02134 0.01366 -0.0989 0.9095 0.1684
-6.000 -0.2959 0.01984 0.01295 -0.1033 0.9053 0.3038
-5.750 -0.2572 0.01984 0.01292 -0.1054 0.9014 0.3639
-5.500 -0.2277 0.01992 0.01280 -0.1058 0.8929 0.3918
-5.250 -0.1903 0.02012 0.01287 -0.1072 0.8886 0.4113
-5.000 -0.1578 0.02025 0.01284 -0.1079 0.8819 0.4264
-4.750 -0.1238 0.02032 0.01272 -0.1090 0.8754 0.4406
-4.500 -0.0864 0.02066 0.01303 -0.1100 0.8714 0.4544
-4.250 -0.0602 0.02099 0.01334 -0.1091 0.8627 0.4645
-4.000 -0.0209 0.02071 0.01283 -0.1116 0.8574 0.4744
-3.750 0.0147 0.02055 0.01260 -0.1128 0.8519 0.4780
-3.500 0.0448 0.02038 0.01233 -0.1132 0.8435 0.4822
-3.250 0.0859 0.01997 0.01172 -0.1160 0.8387 0.4877
-3.000 0.1154 0.01973 0.01134 -0.1167 0.8295 0.4919
-2.750 0.1521 0.01952 0.01105 -0.1182 0.8234 0.4951
-2.500 0.1818 0.01938 0.01083 -0.1186 0.8146 0.4988
-2.250 0.2186 0.01910 0.01042 -0.1205 0.8075 0.5031
-2.000 0.2506 0.01889 0.01007 -0.1216 0.7987 0.5080
-1.750 0.2843 0.01875 0.00989 -0.1226 0.7910 0.5110
-1.500 0.3135 0.01867 0.00975 -0.1228 0.7817 0.5143
-1.250 0.3482 0.01849 0.00949 -0.1242 0.7740 0.5183
-1.000 0.3777 0.01840 0.00929 -0.1248 0.7642 0.5231
-0.750 0.4118 0.01827 0.00910 -0.1259 0.7566 0.5267
-0.500 0.4378 0.01827 0.00910 -0.1255 0.7462 0.5301
-0.250 0.4705 0.01818 0.00895 -0.1264 0.7382 0.5341
0.000 0.4986 0.01816 0.00887 -0.1266 0.7280 0.5384
0.250 0.5288 0.01812 0.00878 -0.1271 0.7191 0.5427
0.500 0.5571 0.01812 0.00879 -0.1271 0.7098 0.5463
0.750 0.5847 0.01815 0.00881 -0.1271 0.7001 0.5507
1.000 0.6158 0.01813 0.00872 -0.1278 0.6916 0.5557
1.250 0.6421 0.01819 0.00879 -0.1275 0.6814 0.5597
1.500 0.6715 0.01821 0.00880 -0.1277 0.6731 0.5637
1.750 0.6970 0.01830 0.00892 -0.1273 0.6629 0.5686
2.000 0.7259 0.01836 0.00895 -0.1276 0.6539 0.5744
2.250 0.7523 0.01843 0.00907 -0.1273 0.6444 0.5785
2.500 0.7784 0.01854 0.00921 -0.1270 0.6349 0.5832
2.750 0.8073 0.01862 0.00928 -0.1271 0.6260 0.5889
3.000 0.8321 0.01876 0.00948 -0.1266 0.6159 0.5941
3.250 0.8597 0.01886 0.00960 -0.1265 0.6071 0.5996
3.500 0.8849 0.01902 0.00981 -0.1261 0.5968 0.6061
3.750 0.9107 0.01916 0.01001 -0.1257 0.5872 0.6116
4.000 0.9367 0.01930 0.01019 -0.1253 0.5777 0.6176
4.250 0.9615 0.01950 0.01044 -0.1249 0.5671 0.6250
4.500 0.9870 0.01965 0.01064 -0.1243 0.5576 0.6311
4.750 1.0111 0.01985 0.01091 -0.1237 0.5467 0.6390
5.000 1.0346 0.02005 0.01121 -0.1229 0.5359 0.6460
5.250 1.0598 0.02024 0.01141 -0.1224 0.5257 0.6543
5.500 1.0820 0.02047 0.01174 -0.1214 0.5142 0.6624
5.750 1.1046 0.02071 0.01208 -0.1204 0.5027 0.6719
6.000 1.1273 0.02094 0.01237 -0.1195 0.4917 0.6812
6.250 1.1493 0.02120 0.01270 -0.1184 0.4800 0.6920
6.500 1.1694 0.02148 0.01310 -0.1171 0.4679 0.7028
6.750 1.1896 0.02176 0.01349 -0.1157 0.4559 0.7147
7.000 1.2096 0.02205 0.01385 -0.1143 0.4440 0.7281
7.250 1.2278 0.02236 0.01426 -0.1126 0.4313 0.7432
7.500 1.2442 0.02269 0.01474 -0.1106 0.4180 0.7601
7.750 1.2593 0.02303 0.01520 -0.1084 0.4048 0.7799
8.250 1.2814 0.02365 0.01605 -0.1024 0.3788 0.8397
8.500 1.2844 0.02376 0.01631 -0.0978 0.3666 1.0000
8.750 1.2989 0.02441 0.01697 -0.0960 0.3514 1.0000
9.000 1.3118 0.02512 0.01769 -0.0940 0.3360 1.0000
9.250 1.3231 0.02591 0.01847 -0.0919 0.3202 1.0000
9.500 1.3329 0.02678 0.01935 -0.0896 0.3042 1.0000
9.750 1.3415 0.02776 0.02033 -0.0873 0.2882 1.0000
10.000 1.3485 0.02885 0.02141 -0.0850 0.2722 1.0000
10.250 1.3545 0.03007 0.02262 -0.0827 0.2565 1.0000
10.500 1.3593 0.03143 0.02397 -0.0804 0.2411 1.0000
10.750 1.3633 0.03292 0.02546 -0.0783 0.2263 1.0000
11.000 1.3667 0.03454 0.02710 -0.0763 0.2122 1.0000
11.250 1.3695 0.03630 0.02889 -0.0744 0.1989 1.0000
11.500 1.3717 0.03820 0.03081 -0.0727 0.1866 1.0000
11.750 1.3730 0.04027 0.03289 -0.0712 0.1752 1.0000
12.000 1.3726 0.04256 0.03517 -0.0697 0.1650 1.0000
12.250 1.3740 0.04483 0.03752 -0.0686 0.1543 1.0000
12.500 1.3742 0.04730 0.04004 -0.0676 0.1449 1.0000
12.750 1.3719 0.05008 0.04282 -0.0667 0.1367 1.0000
13.000 1.3728 0.05271 0.04557 -0.0661 0.1279 1.0000
13.250 1.3705 0.05574 0.04863 -0.0656 0.1209 1.0000
13.500 1.3698 0.05872 0.05173 -0.0654 0.1134 1.0000
13.750 1.3669 0.06204 0.05509 -0.0653 0.1073 1.0000
14.000 1.3658 0.06531 0.05847 -0.0653 0.1008 1.0000
14.250 1.3614 0.06902 0.06219 -0.0656 0.0958 1.0000
14.500 1.3608 0.07245 0.06578 -0.0660 0.0898 1.0000
14.750 1.3561 0.07644 0.06981 -0.0666 0.0853 1.0000
15.000 1.3542 0.08019 0.07368 -0.0673 0.0806 1.0000
15.250 1.3509 0.08423 0.07783 -0.0682 0.0761 1.0000
15.750 1.3442 0.09254 0.08635 -0.0704 0.0685 1.0000
16.000 1.3402 0.09693 0.09085 -0.0718 0.0650 1.0000
16.500 1.3335 0.10565 0.09976 -0.0748 0.0589 1.0000
16.750 1.3301 0.11016 0.10440 -0.0766 0.0561 1.0000
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Polar data table (+)
Polar graphs
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