EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 100,000 Max Cl/Cd: 45.39 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e553-il-100000.txt Download as CSV file: xf-e553-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2381 0.14068 0.13596 -0.0460 1.0000 0.1255
-13.750 -0.2667 0.13952 0.13486 -0.0490 1.0000 0.1312
-13.500 -0.4546 0.10834 0.10319 -0.0645 1.0000 0.0553
-13.250 -0.4492 0.10496 0.09985 -0.0642 1.0000 0.0543
-13.000 -0.4627 0.09824 0.09315 -0.0667 1.0000 0.0528
-12.750 -0.5091 0.08700 0.08184 -0.0731 1.0000 0.0504
-12.500 -0.6136 0.07376 0.06814 -0.0824 1.0000 0.0472
-12.250 -0.6486 0.07038 0.06458 -0.0833 1.0000 0.0466
-12.000 -0.6593 0.06657 0.06067 -0.0828 1.0000 0.0463
-11.750 -0.6734 0.06338 0.05742 -0.0818 1.0000 0.0460
-11.500 -0.6916 0.06072 0.05471 -0.0799 1.0000 0.0457
-11.250 -0.7159 0.05878 0.05272 -0.0766 1.0000 0.0455
-11.000 -0.7408 0.05758 0.05151 -0.0721 1.0000 0.0453
-10.750 -0.7687 0.05660 0.05049 -0.0670 1.0000 0.0452
-10.500 -0.7898 0.05512 0.04892 -0.0627 1.0000 0.0450
-10.250 -0.8060 0.05345 0.04712 -0.0590 1.0000 0.0447
-10.000 -0.8191 0.05153 0.04503 -0.0557 1.0000 0.0446
-9.750 -0.8273 0.04950 0.04279 -0.0528 1.0000 0.0445
-9.500 -0.8314 0.04738 0.04044 -0.0502 1.0000 0.0447
-9.250 -0.8032 0.04429 0.03683 -0.0533 0.9937 0.0458
-9.000 -0.7733 0.04134 0.03367 -0.0557 0.9873 0.0480
-8.750 -0.7368 0.03937 0.03165 -0.0585 0.9818 0.0512
-8.500 -0.7041 0.03739 0.02942 -0.0599 0.9748 0.0540
-8.250 -0.6657 0.03537 0.02747 -0.0619 0.9703 0.0591
-8.000 -0.6373 0.03407 0.02605 -0.0629 0.9618 0.0661
-7.750 -0.6031 0.03254 0.02464 -0.0647 0.9560 0.0770
-7.500 -0.5817 0.03094 0.02332 -0.0648 0.9469 0.0919
-7.250 -0.5592 0.02914 0.02173 -0.0661 0.9385 0.1180
-7.000 -0.5417 0.02559 0.01890 -0.0692 0.9296 0.1920
-6.750 -0.5211 0.02496 0.01942 -0.0700 0.9193 0.4069
-6.500 -0.4764 0.02749 0.02187 -0.0703 0.9130 0.4453
-6.250 -0.4489 0.02938 0.02371 -0.0682 0.9034 0.4642
-6.000 -0.4051 0.03166 0.02594 -0.0678 0.8978 0.4829
-5.750 -0.3741 0.03370 0.02795 -0.0653 0.8899 0.4951
-5.500 -0.3356 0.03517 0.02933 -0.0645 0.8834 0.5087
-5.250 -0.2857 0.03630 0.03031 -0.0658 0.8803 0.5234
-5.000 -0.2648 0.03749 0.03146 -0.0624 0.8703 0.5323
-4.750 -0.2162 0.03824 0.03208 -0.0633 0.8666 0.5435
-4.500 -0.1692 0.03745 0.03108 -0.0674 0.8633 0.5562
-4.250 -0.1539 0.03783 0.03142 -0.0641 0.8524 0.5614
-4.000 -0.1151 0.03612 0.02948 -0.0690 0.8478 0.5719
-3.750 -0.0991 0.03630 0.02962 -0.0662 0.8375 0.5757
-3.500 -0.0596 0.03536 0.02853 -0.0692 0.8326 0.5823
-3.250 -0.0466 0.03426 0.02729 -0.0696 0.8221 0.5887
-3.000 -0.0087 0.03391 0.02685 -0.0706 0.8170 0.5925
-2.750 0.0155 0.03335 0.02619 -0.0710 0.8093 0.5973
-2.500 0.0439 0.03200 0.02463 -0.0744 0.8013 0.6040
-2.250 0.0847 0.03151 0.02407 -0.0758 0.7976 0.6071
-2.000 0.0944 0.03147 0.02400 -0.0736 0.7864 0.6102
-1.750 0.1348 0.03066 0.02305 -0.0765 0.7821 0.6151
-1.500 0.1510 0.03018 0.02245 -0.0770 0.7715 0.6206
-1.250 0.1867 0.02970 0.02192 -0.0780 0.7667 0.6234
-1.000 0.2026 0.02974 0.02194 -0.0766 0.7574 0.6266
-0.750 0.2370 0.02925 0.02135 -0.0783 0.7516 0.6314
-0.500 0.2673 0.02879 0.02076 -0.0803 0.7447 0.6370
-0.250 0.2898 0.02872 0.02070 -0.0795 0.7369 0.6398
0.000 0.3279 0.02824 0.02016 -0.0811 0.7328 0.6435
0.250 0.3403 0.02854 0.02046 -0.0796 0.7225 0.6479
0.500 0.3808 0.02796 0.01975 -0.0825 0.7178 0.6538
0.750 0.3943 0.02832 0.02017 -0.0805 0.7090 0.6569
1.000 0.4258 0.02809 0.01991 -0.0812 0.7032 0.6609
1.250 0.4677 0.02756 0.01929 -0.0838 0.6996 0.6663
1.500 0.4772 0.02816 0.01992 -0.0820 0.6890 0.6710
1.750 0.5125 0.02782 0.01958 -0.0829 0.6849 0.6754
2.000 0.5240 0.02844 0.02026 -0.0811 0.6755 0.6801
2.250 0.5616 0.02814 0.01988 -0.0834 0.6704 0.6861
2.500 0.5887 0.02815 0.01993 -0.0831 0.6651 0.6903
2.750 0.6023 0.02872 0.02059 -0.0815 0.6564 0.6955
3.000 0.6442 0.02829 0.02009 -0.0840 0.6524 0.7026
3.250 0.6482 0.02927 0.02121 -0.0809 0.6431 0.7069
3.500 0.6825 0.02905 0.02101 -0.0819 0.6382 0.7130
3.750 0.7263 0.02855 0.02047 -0.0844 0.6349 0.7201
4.000 0.7223 0.02990 0.02198 -0.0804 0.6242 0.7253
4.250 0.7644 0.02942 0.02150 -0.0825 0.6204 0.7337
4.500 0.7640 0.03071 0.02293 -0.0791 0.6107 0.7394
4.750 0.8007 0.03036 0.02261 -0.0803 0.6060 0.7474
5.000 0.8454 0.02969 0.02196 -0.0823 0.6027 0.7558
5.250 0.8365 0.03138 0.02383 -0.0780 0.5917 0.7637
5.500 0.8804 0.03063 0.02311 -0.0798 0.5880 0.7735
5.750 0.8744 0.03232 0.02496 -0.0760 0.5776 0.7832
6.000 0.9140 0.03164 0.02435 -0.0771 0.5734 0.7938
6.250 0.9170 0.03283 0.02568 -0.0742 0.5647 0.8048
6.500 0.9476 0.03259 0.02554 -0.0742 0.5587 0.8187
6.750 0.9980 0.03135 0.02434 -0.0764 0.5551 0.8351
7.000 0.9781 0.03333 0.02655 -0.0705 0.5440 0.8516
7.250 1.0274 0.03184 0.02513 -0.0721 0.5400 0.8746
7.500 1.0044 0.03364 0.02719 -0.0656 0.5295 0.9082
7.750 1.0765 0.03159 0.02522 -0.0711 0.5244 1.0000
8.000 1.0913 0.03289 0.02660 -0.0714 0.5138 1.0000
8.250 1.1641 0.03112 0.02475 -0.0773 0.5075 1.0000
8.500 1.1682 0.03237 0.02611 -0.0751 0.4966 1.0000
8.750 1.2208 0.03127 0.02498 -0.0781 0.4884 1.0000
9.000 1.2423 0.03142 0.02518 -0.0773 0.4779 1.0000
9.250 1.2584 0.03179 0.02562 -0.0757 0.4674 1.0000
9.500 1.3054 0.03076 0.02455 -0.0778 0.4571 1.0000
9.750 1.3226 0.03087 0.02472 -0.0761 0.4455 1.0000
10.000 1.3330 0.03124 0.02518 -0.0735 0.4336 1.0000
10.250 1.3536 0.03111 0.02508 -0.0722 0.4213 1.0000
10.500 1.3757 0.03086 0.02481 -0.0709 0.4083 1.0000
10.750 1.3935 0.03070 0.02465 -0.0691 0.3947 1.0000
11.000 1.3964 0.03109 0.02507 -0.0654 0.3813 1.0000
11.250 1.3932 0.03182 0.02589 -0.0613 0.3677 1.0000
11.500 1.3923 0.03258 0.02668 -0.0578 0.3534 1.0000
11.750 1.3911 0.03350 0.02762 -0.0546 0.3384 1.0000
12.000 1.3885 0.03463 0.02876 -0.0516 0.3228 1.0000
12.250 1.3846 0.03603 0.03014 -0.0487 0.3068 1.0000
12.500 1.3801 0.03766 0.03175 -0.0462 0.2903 1.0000
12.750 1.3757 0.03948 0.03349 -0.0440 0.2735 1.0000
13.000 1.3699 0.04161 0.03555 -0.0420 0.2568 1.0000
13.250 1.3618 0.04415 0.03804 -0.0402 0.2405 1.0000
13.500 1.3543 0.04682 0.04067 -0.0387 0.2247 1.0000
13.750 1.3472 0.04963 0.04343 -0.0376 0.2095 1.0000
14.000 1.3409 0.05254 0.04627 -0.0366 0.1949 1.0000
14.250 1.3355 0.05551 0.04916 -0.0359 0.1811 1.0000
14.500 1.3317 0.05844 0.05199 -0.0353 0.1679 1.0000
14.750 1.3249 0.06185 0.05543 -0.0350 0.1561 1.0000
15.000 1.3195 0.06528 0.05889 -0.0348 0.1448 1.0000
15.250 1.3166 0.06854 0.06214 -0.0347 0.1342 1.0000
15.500 1.3165 0.07149 0.06500 -0.0346 0.1241 1.0000
15.750 1.3129 0.07498 0.06853 -0.0349 0.1155 1.0000
16.000 1.3103 0.07852 0.07214 -0.0351 0.1074 1.0000
16.250 1.3166 0.08088 0.07433 -0.0350 0.0990 1.0000
16.500 1.3086 0.08527 0.07896 -0.0359 0.0932 1.0000
16.750 1.3164 0.08756 0.08112 -0.0358 0.0862 1.0000
17.000 1.3085 0.09210 0.08592 -0.0369 0.0818 1.0000
17.250 1.3224 0.09362 0.08722 -0.0365 0.0753 1.0000
17.500 1.3109 0.09881 0.09274 -0.0382 0.0725 1.0000
17.750 1.3061 0.10305 0.09714 -0.0395 0.0689 1.0000
18.000 1.3198 0.10469 0.09864 -0.0392 0.0642 1.0000
18.250 1.3051 0.11055 0.10483 -0.0416 0.0625 1.0000
18.500 1.2930 0.11617 0.11071 -0.0440 0.0606 1.0000
18.750 1.2834 0.12145 0.11617 -0.0464 0.0587 1.0000
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Polar data table (+)
Polar graphs
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