EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 500,000 Max Cl/Cd: 112.99 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e407-il-500000.txt Download as CSV file: xf-e407-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 407 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2561 0.08756 0.08534 -0.0949 0.9727 0.0200
-11.500 -0.2647 0.07935 0.07713 -0.0989 0.9722 0.0202
-11.250 -0.3187 0.06152 0.05911 -0.1102 0.9715 0.0199
-11.000 -0.3417 0.05363 0.05107 -0.1160 0.9707 0.0197
-9.250 -0.4987 0.03742 0.03336 -0.1216 0.9448 0.0143
-9.000 -0.5280 0.02984 0.02506 -0.1134 0.9361 0.0079
-8.750 -0.5098 0.02694 0.02181 -0.1136 0.9343 0.0076
-8.500 -0.4856 0.02481 0.01942 -0.1142 0.9331 0.0074
-8.250 -0.4600 0.02315 0.01755 -0.1148 0.9322 0.0075
-8.000 -0.4325 0.02182 0.01609 -0.1158 0.9314 0.0076
-7.750 -0.4369 0.02133 0.01553 -0.1104 0.9235 0.0076
-7.500 -0.4109 0.02028 0.01438 -0.1111 0.9218 0.0081
-7.250 -0.3821 0.01929 0.01330 -0.1123 0.9206 0.0084
-7.000 -0.3508 0.01847 0.01239 -0.1139 0.9197 0.0090
-6.750 -0.3186 0.01718 0.01102 -0.1163 0.9189 0.0110
-6.500 -0.2841 0.01652 0.01030 -0.1184 0.9183 0.0129
-6.250 -0.2764 0.01612 0.00988 -0.1153 0.9119 0.0171
-6.000 -0.2458 0.01541 0.00920 -0.1168 0.9100 0.0301
-5.750 -0.2121 0.01480 0.00870 -0.1188 0.9088 0.0511
-5.500 -0.1766 0.01406 0.00818 -0.1215 0.9080 0.0980
-5.250 -0.1389 0.01314 0.00764 -0.1249 0.9074 0.1863
-5.000 -0.0973 0.01190 0.00700 -0.1297 0.9072 0.3334
-4.750 -0.0564 0.01106 0.00670 -0.1336 0.9069 0.4823
-4.500 -0.0202 0.01093 0.00659 -0.1355 0.9063 0.5221
-4.250 0.0163 0.01087 0.00649 -0.1374 0.9058 0.5467
-4.000 0.0530 0.01087 0.00648 -0.1392 0.9054 0.5666
-3.750 0.0899 0.01085 0.00641 -0.1411 0.9049 0.5784
-3.500 0.1267 0.01085 0.00632 -0.1430 0.9044 0.5885
-3.250 0.1335 0.01116 0.00666 -0.1388 0.8970 0.5940
-3.000 0.1674 0.01115 0.00660 -0.1401 0.8956 0.6018
-2.750 0.2023 0.01111 0.00653 -0.1415 0.8946 0.6074
-2.500 0.2384 0.01105 0.00646 -0.1432 0.8936 0.6134
-2.250 0.2754 0.01095 0.00630 -0.1452 0.8928 0.6192
-2.000 0.3116 0.01086 0.00623 -0.1468 0.8919 0.6242
-1.750 0.3493 0.01079 0.00612 -0.1488 0.8911 0.6310
-1.500 0.3861 0.01064 0.00597 -0.1507 0.8902 0.6346
-1.250 0.3996 0.01079 0.00614 -0.1478 0.8833 0.6369
-1.000 0.4341 0.01062 0.00597 -0.1492 0.8812 0.6395
-0.750 0.4713 0.01041 0.00573 -0.1512 0.8794 0.6424
-0.500 0.5092 0.01019 0.00548 -0.1533 0.8778 0.6454
-0.250 0.5476 0.00998 0.00525 -0.1556 0.8763 0.6479
0.000 0.5663 0.01001 0.00533 -0.1537 0.8699 0.6499
0.250 0.5984 0.00986 0.00519 -0.1546 0.8665 0.6521
0.500 0.6351 0.00965 0.00498 -0.1564 0.8638 0.6546
0.750 0.6646 0.00955 0.00489 -0.1568 0.8592 0.6574
1.000 0.6914 0.00947 0.00481 -0.1567 0.8535 0.6601
1.250 0.7267 0.00928 0.00462 -0.1582 0.8497 0.6624
1.500 0.7512 0.00922 0.00462 -0.1575 0.8434 0.6645
1.750 0.7810 0.00909 0.00451 -0.1578 0.8372 0.6666
2.000 0.8081 0.00900 0.00446 -0.1577 0.8299 0.6690
2.250 0.8370 0.00891 0.00437 -0.1578 0.8223 0.6717
2.500 0.8622 0.00888 0.00435 -0.1573 0.8133 0.6746
2.750 0.8911 0.00879 0.00428 -0.1575 0.8042 0.6769
3.000 0.9177 0.00873 0.00425 -0.1572 0.7926 0.6788
3.250 0.9419 0.00872 0.00426 -0.1564 0.7786 0.6810
3.500 0.9651 0.00875 0.00430 -0.1553 0.7622 0.6836
3.750 0.9880 0.00882 0.00435 -0.1543 0.7419 0.6864
4.000 1.0101 0.00894 0.00440 -0.1530 0.7152 0.6892
4.250 1.0285 0.00916 0.00448 -0.1510 0.6807 0.6914
4.500 1.0423 0.00946 0.00465 -0.1481 0.6422 0.6935
4.750 1.0508 0.00987 0.00489 -0.1441 0.6007 0.6959
5.000 1.0586 0.01038 0.00522 -0.1401 0.5579 0.6987
5.250 1.0672 0.01098 0.00562 -0.1364 0.5139 0.7016
5.500 1.0780 0.01159 0.00604 -0.1333 0.4714 0.7044
5.750 1.0877 0.01225 0.00650 -0.1301 0.4262 0.7066
6.000 1.0983 0.01296 0.00701 -0.1271 0.3796 0.7089
6.250 1.1114 0.01362 0.00751 -0.1246 0.3394 0.7115
6.500 1.1251 0.01432 0.00805 -0.1224 0.3008 0.7145
6.750 1.1389 0.01509 0.00861 -0.1202 0.2594 0.7176
7.000 1.1533 0.01584 0.00917 -0.1182 0.2202 0.7203
7.250 1.1680 0.01657 0.00977 -0.1163 0.1878 0.7227
7.500 1.1836 0.01729 0.01037 -0.1146 0.1587 0.7254
7.750 1.1987 0.01807 0.01102 -0.1128 0.1307 0.7284
8.250 1.2300 0.01961 0.01239 -0.1095 0.0869 0.7346
8.500 1.2443 0.02046 0.01316 -0.1077 0.0689 0.7374
8.750 1.2589 0.02131 0.01397 -0.1060 0.0543 0.7404
9.000 1.2732 0.02222 0.01484 -0.1042 0.0428 0.7437
9.250 1.2861 0.02327 0.01586 -0.1023 0.0341 0.7469
9.500 1.3022 0.02403 0.01669 -0.1008 0.0296 0.7499
9.750 1.3115 0.02534 0.01803 -0.0984 0.0245 0.7530
10.000 1.3281 0.02605 0.01884 -0.0971 0.0224 0.7568
10.250 1.3423 0.02702 0.01986 -0.0956 0.0200 0.7607
10.500 1.3468 0.02876 0.02169 -0.0928 0.0173 0.7639
10.750 1.3627 0.02954 0.02259 -0.0916 0.0162 0.7675
11.000 1.3772 0.03048 0.02360 -0.0902 0.0145 0.7714
11.250 1.3872 0.03183 0.02499 -0.0885 0.0128 0.7756
11.500 1.3913 0.03369 0.02698 -0.0861 0.0115 0.7793
11.750 1.4030 0.03488 0.02830 -0.0846 0.0105 0.7837
12.000 1.4133 0.03626 0.02975 -0.0831 0.0096 0.7886
12.250 1.4195 0.03800 0.03158 -0.0813 0.0087 0.7931
12.500 1.4113 0.04123 0.03499 -0.0783 0.0079 0.7969
12.750 1.4202 0.04287 0.03676 -0.0770 0.0075 0.8023
13.000 1.4260 0.04486 0.03893 -0.0756 0.0070 0.8074
13.250 1.4308 0.04697 0.04118 -0.0742 0.0066 0.8132
13.500 1.4353 0.04920 0.04352 -0.0731 0.0062 0.8199
13.750 1.4385 0.05158 0.04603 -0.0720 0.0059 0.8268
14.000 1.4375 0.05457 0.04915 -0.0710 0.0056 0.8344
14.250 1.4272 0.05884 0.05362 -0.0698 0.0053 0.8412
14.500 1.4195 0.06306 0.05806 -0.0690 0.0051 0.8493
14.750 1.4211 0.06605 0.06124 -0.0688 0.0050 0.8617
15.000 1.4201 0.06939 0.06478 -0.0686 0.0048 0.8783
15.500 1.4067 0.07659 0.07238 -0.0676 0.0046 1.0000
15.750 1.4020 0.08119 0.07714 -0.0687 0.0044 1.0000
16.000 1.3969 0.08601 0.08211 -0.0701 0.0043 1.0000
16.250 1.3889 0.09145 0.08771 -0.0719 0.0042 1.0000
16.500 1.3801 0.09721 0.09363 -0.0741 0.0042 1.0000
16.750 1.3696 0.10349 0.10008 -0.0768 0.0041 1.0000
17.000 1.3587 0.11003 0.10679 -0.0799 0.0041 1.0000
17.250 1.3466 0.11699 0.11393 -0.0835 0.0041 1.0000
17.500 1.3338 0.12429 0.12139 -0.0876 0.0040 1.0000
17.750 1.3208 0.13186 0.12912 -0.0920 0.0040 1.0000
18.000 1.3063 0.13996 0.13740 -0.0970 0.0040 1.0000
18.250 1.2912 0.14847 0.14608 -0.1024 0.0041 1.0000
18.500 1.2750 0.15751 0.15530 -0.1084 0.0041 1.0000
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