EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 50,000 Max Cl/Cd: 30.15 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e360-il-50000.txt Download as CSV file: xf-e360-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4802 0.13093 0.12376 -0.0039 1.0000 0.2336
-10.750 -0.4608 0.12592 0.11875 -0.0032 1.0000 0.2417
-10.500 -0.4835 0.12485 0.11783 -0.0055 1.0000 0.2507
-10.250 -0.4678 0.12058 0.11356 -0.0046 1.0000 0.2649
-10.000 -0.4499 0.11623 0.10923 -0.0038 1.0000 0.2773
-9.750 -0.4427 0.11278 0.10582 -0.0035 1.0000 0.2902
-9.500 -0.4379 0.10952 0.10262 -0.0031 1.0000 0.3068
-9.250 -0.4328 0.10624 0.09940 -0.0027 1.0000 0.3224
-9.000 -0.4277 0.10310 0.09630 -0.0021 1.0000 0.3388
-8.750 -0.4224 0.09984 0.09309 -0.0016 1.0000 0.3544
-8.500 -0.4171 0.09660 0.08992 -0.0010 1.0000 0.3700
-8.250 -0.4121 0.09336 0.08674 -0.0003 1.0000 0.3858
-8.000 -0.4071 0.09009 0.08353 0.0003 1.0000 0.4008
-7.750 -0.4032 0.08683 0.08034 0.0010 1.0000 0.4152
-7.250 -0.5886 0.06329 0.05653 -0.0257 1.0000 0.1536
-7.000 -0.6115 0.05859 0.05096 -0.0226 1.0000 0.1268
-6.750 -0.5971 0.05415 0.04665 -0.0214 1.0000 0.1230
-6.500 -0.5943 0.05060 0.04283 -0.0188 1.0000 0.1180
-6.250 -0.5948 0.04777 0.03926 -0.0149 1.0000 0.1111
-6.000 -0.5865 0.04484 0.03615 -0.0123 1.0000 0.1100
-5.750 -0.5784 0.04217 0.03321 -0.0094 1.0000 0.1089
-5.500 -0.5689 0.03973 0.03048 -0.0066 1.0000 0.1076
-5.250 -0.5579 0.03744 0.02787 -0.0038 1.0000 0.1069
-5.000 -0.5453 0.03547 0.02556 -0.0012 1.0000 0.1079
-4.750 -0.5318 0.03390 0.02357 0.0013 1.0000 0.1109
-4.500 -0.5152 0.03194 0.02154 0.0030 1.0000 0.1163
-4.250 -0.4962 0.03042 0.01988 0.0047 1.0000 0.1227
-4.000 -0.4756 0.02891 0.01835 0.0061 1.0000 0.1346
-3.750 -0.0241 0.02520 0.01646 -0.0398 1.0000 1.0000
-3.500 -0.0152 0.02472 0.01589 -0.0385 1.0000 1.0000
-3.250 -0.0087 0.02441 0.01553 -0.0369 1.0000 1.0000
-3.000 -0.0068 0.02433 0.01542 -0.0345 1.0000 1.0000
-2.750 -0.0142 0.02457 0.01567 -0.0308 1.0000 1.0000
-2.500 -0.0296 0.02506 0.01614 -0.0261 1.0000 1.0000
-2.250 -0.0440 0.02552 0.01656 -0.0217 1.0000 1.0000
-2.000 -0.0553 0.02589 0.01687 -0.0177 1.0000 1.0000
-1.750 -0.0639 0.02619 0.01712 -0.0141 1.0000 1.0000
-1.500 -0.0704 0.02644 0.01728 -0.0107 1.0000 1.0000
-1.250 -0.0753 0.02665 0.01742 -0.0075 1.0000 1.0000
-1.000 -0.0789 0.02684 0.01752 -0.0044 1.0000 1.0000
-0.750 -0.0339 0.02729 0.01780 -0.0098 0.9881 1.0000
-0.500 0.0080 0.02774 0.01809 -0.0145 0.9761 1.0000
-0.250 0.0442 0.02818 0.01841 -0.0180 0.9644 1.0000
0.000 0.0787 0.02863 0.01876 -0.0211 0.9527 1.0000
0.250 0.1133 0.02913 0.01917 -0.0240 0.9417 1.0000
0.500 0.1500 0.02964 0.01961 -0.0272 0.9306 1.0000
0.750 0.1712 0.03013 0.02005 -0.0276 0.9186 1.0000
1.000 0.1959 0.03068 0.02056 -0.0285 0.9072 1.0000
1.250 0.2309 0.03126 0.02112 -0.0310 0.8960 1.0000
1.500 0.2569 0.03184 0.02168 -0.0319 0.8839 1.0000
1.750 0.2729 0.03246 0.02229 -0.0310 0.8710 1.0000
2.000 0.2945 0.03310 0.02293 -0.0310 0.8580 1.0000
2.250 0.3225 0.03371 0.02357 -0.0318 0.8444 1.0000
2.500 0.3544 0.03429 0.02418 -0.0330 0.8300 1.0000
2.750 0.3876 0.03481 0.02475 -0.0342 0.8143 1.0000
3.000 0.4198 0.03526 0.02527 -0.0350 0.7974 1.0000
3.250 0.4558 0.03556 0.02567 -0.0360 0.7788 1.0000
3.500 0.5069 0.03529 0.02552 -0.0384 0.7581 1.0000
3.750 0.5681 0.03429 0.02470 -0.0409 0.7366 1.0000
4.000 0.5806 0.03456 0.02503 -0.0376 0.7149 1.0000
4.250 0.6244 0.03352 0.02410 -0.0371 0.6926 1.0000
4.500 0.6527 0.03288 0.02358 -0.0347 0.6698 1.0000
4.750 0.6805 0.03207 0.02285 -0.0320 0.6456 1.0000
5.000 0.7048 0.03132 0.02217 -0.0289 0.6198 1.0000
5.250 0.7363 0.02998 0.02088 -0.0261 0.5920 1.0000
5.500 0.7585 0.02909 0.01999 -0.0225 0.5595 1.0000
5.750 0.7780 0.02829 0.01914 -0.0187 0.5217 1.0000
6.000 0.7986 0.02752 0.01822 -0.0151 0.4805 1.0000
6.250 0.8172 0.02714 0.01756 -0.0117 0.4391 1.0000
6.500 0.8304 0.02754 0.01777 -0.0084 0.4016 1.0000
6.750 0.8463 0.02821 0.01821 -0.0058 0.3706 1.0000
7.000 0.8640 0.02908 0.01886 -0.0037 0.3447 1.0000
7.250 0.8801 0.03028 0.02000 -0.0016 0.3233 1.0000
7.500 0.8992 0.03155 0.02117 -0.0001 0.3052 1.0000
7.750 0.9178 0.03292 0.02251 0.0014 0.2893 1.0000
8.000 0.9341 0.03457 0.02425 0.0030 0.2762 1.0000
8.250 0.9502 0.03635 0.02614 0.0046 0.2648 1.0000
8.500 0.9689 0.03810 0.02791 0.0058 0.2538 1.0000
8.750 0.9828 0.04004 0.03006 0.0074 0.2444 1.0000
9.000 0.9931 0.04242 0.03267 0.0093 0.2370 1.0000
9.250 1.0086 0.04444 0.03479 0.0106 0.2283 1.0000
9.500 1.0110 0.04722 0.03789 0.0130 0.2225 1.0000
9.750 1.0070 0.05038 0.04141 0.0156 0.2183 1.0000
10.000 1.0338 0.05261 0.04354 0.0156 0.2107 1.0000
10.250 1.0134 0.05647 0.04785 0.0190 0.2088 1.0000
10.500 0.9866 0.06084 0.05253 0.0220 0.2078 1.0000
10.750 0.9512 0.06578 0.05766 0.0247 0.2082 1.0000
11.000 0.9100 0.07167 0.06362 0.0259 0.2096 1.0000
11.250 0.8724 0.07913 0.07110 0.0244 0.2109 1.0000
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Polar data table (+)
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