EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 100,000 Max Cl/Cd: 45.59 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e337-il-100000-n5.txt Download as CSV file: xf-e337-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 337 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3766 0.09686 0.09227 -0.0228 1.0000 0.0499
-9.000 -0.3778 0.09297 0.08844 -0.0249 1.0000 0.0505
-8.750 -0.3814 0.08880 0.08434 -0.0275 1.0000 0.0510
-8.500 -0.3878 0.08450 0.08011 -0.0306 1.0000 0.0513
-8.250 -0.3980 0.08052 0.07617 -0.0323 1.0000 0.0516
-7.750 -0.3809 0.05720 0.05302 -0.0354 1.0000 0.0290
-7.500 -0.4553 0.06573 0.06095 -0.0284 1.0000 0.0293
-7.250 -0.4484 0.06348 0.05888 -0.0269 1.0000 0.0285
-6.750 -0.4147 0.05212 0.04681 -0.0310 0.9033 0.0232
-6.500 -0.3917 0.04837 0.04275 -0.0326 0.8663 0.0227
-6.250 -0.3756 0.04508 0.03907 -0.0320 0.8334 0.0222
-6.000 -0.3623 0.04209 0.03568 -0.0302 0.8061 0.0216
-5.750 -0.3492 0.03918 0.03231 -0.0279 0.7830 0.0212
-5.500 -0.3345 0.03647 0.02915 -0.0255 0.7624 0.0207
-5.250 -0.3181 0.03381 0.02599 -0.0232 0.7441 0.0204
-5.000 -0.2991 0.03146 0.02315 -0.0212 0.7272 0.0203
-4.750 -0.2777 0.02936 0.02059 -0.0195 0.7113 0.0203
-4.500 -0.2539 0.02758 0.01841 -0.0183 0.6961 0.0205
-4.250 -0.2285 0.02609 0.01656 -0.0174 0.6814 0.0215
-4.000 -0.2011 0.02471 0.01478 -0.0167 0.6677 0.0231
-3.750 -0.1745 0.02356 0.01346 -0.0163 0.6547 0.0248
-3.500 -0.1473 0.02253 0.01226 -0.0158 0.6425 0.0264
-3.250 -0.1200 0.02145 0.01101 -0.0153 0.6299 0.0280
-3.000 -0.0950 0.02053 0.00999 -0.0144 0.6187 0.0300
-2.750 -0.0714 0.01995 0.00933 -0.0135 0.6083 0.0342
-2.500 -0.0489 0.01929 0.00861 -0.0123 0.5975 0.0403
-2.250 -0.0260 0.01874 0.00798 -0.0111 0.5877 0.0500
-2.000 0.0619 0.01577 0.00820 -0.0211 0.5753 0.7637
-1.750 0.0751 0.01686 0.00912 -0.0161 0.5663 0.8798
-1.500 0.1880 0.01839 0.01005 -0.0295 0.5515 0.9540
-1.250 0.2440 0.01827 0.00959 -0.0350 0.5415 0.9716
-1.000 0.2750 0.01816 0.00927 -0.0359 0.5329 0.9762
-0.750 0.3077 0.01801 0.00892 -0.0371 0.5249 0.9801
-0.500 0.3377 0.01794 0.00867 -0.0378 0.5168 0.9842
-0.250 0.3690 0.01784 0.00840 -0.0389 0.5098 0.9875
0.000 0.4004 0.01774 0.00817 -0.0399 0.5024 0.9908
0.250 0.4304 0.01770 0.00797 -0.0406 0.4961 0.9940
0.500 0.4612 0.01762 0.00782 -0.0416 0.4887 0.9968
0.750 0.4918 0.01758 0.00764 -0.0425 0.4829 0.9996
1.000 0.5159 0.01766 0.00766 -0.0421 0.4768 1.0000
1.250 0.5388 0.01775 0.00769 -0.0414 0.4710 1.0000
1.500 0.5616 0.01786 0.00768 -0.0406 0.4662 1.0000
1.750 0.5845 0.01799 0.00781 -0.0399 0.4602 1.0000
2.000 0.6074 0.01813 0.00790 -0.0392 0.4551 1.0000
2.250 0.6303 0.01826 0.00795 -0.0385 0.4508 1.0000
2.500 0.6530 0.01843 0.00814 -0.0378 0.4452 1.0000
2.750 0.6758 0.01860 0.00830 -0.0371 0.4401 1.0000
3.000 0.6986 0.01876 0.00841 -0.0363 0.4359 1.0000
3.250 0.7212 0.01897 0.00864 -0.0356 0.4312 1.0000
3.500 0.7436 0.01917 0.00887 -0.0348 0.4259 1.0000
3.750 0.7663 0.01937 0.00904 -0.0341 0.4217 1.0000
4.000 0.7888 0.01959 0.00926 -0.0333 0.4176 1.0000
4.250 0.8107 0.01985 0.00962 -0.0325 0.4125 1.0000
4.500 0.8328 0.02008 0.00987 -0.0317 0.4079 1.0000
4.750 0.8553 0.02029 0.01004 -0.0309 0.4042 1.0000
5.000 0.8765 0.02061 0.01049 -0.0299 0.3993 1.0000
5.250 0.8977 0.02089 0.01086 -0.0290 0.3944 1.0000
5.500 0.9196 0.02113 0.01111 -0.0281 0.3903 1.0000
5.750 0.9409 0.02144 0.01147 -0.0272 0.3863 1.0000
6.000 0.9606 0.02181 0.01199 -0.0261 0.3810 1.0000
6.250 0.9813 0.02210 0.01234 -0.0250 0.3765 1.0000
6.500 1.0032 0.02235 0.01258 -0.0241 0.3729 1.0000
6.750 1.0210 0.02281 0.01325 -0.0227 0.3674 1.0000
7.000 1.0402 0.02316 0.01370 -0.0215 0.3625 1.0000
7.250 1.0611 0.02342 0.01397 -0.0204 0.3584 1.0000
7.500 1.0780 0.02388 0.01462 -0.0188 0.3530 1.0000
7.750 1.0955 0.02426 0.01512 -0.0173 0.3475 1.0000
8.000 1.1156 0.02447 0.01534 -0.0161 0.3429 1.0000
8.250 1.1297 0.02500 0.01610 -0.0142 0.3369 1.0000
8.500 1.1461 0.02536 0.01657 -0.0125 0.3314 1.0000
8.750 1.1649 0.02560 0.01683 -0.0110 0.3268 1.0000
9.000 1.1754 0.02623 0.01771 -0.0086 0.3204 1.0000
9.250 1.1908 0.02652 0.01810 -0.0067 0.3148 1.0000
9.500 1.2025 0.02697 0.01869 -0.0043 0.3088 1.0000
9.750 1.2126 0.02740 0.01928 -0.0017 0.3021 1.0000
10.000 1.2245 0.02770 0.01964 0.0007 0.2961 1.0000
10.250 1.2289 0.02831 0.02045 0.0040 0.2891 1.0000
10.500 1.2397 0.02852 0.02069 0.0067 0.2833 1.0000
10.750 1.2370 0.02930 0.02168 0.0109 0.2761 1.0000
11.000 1.2411 0.02964 0.02208 0.0145 0.2700 1.0000
11.250 1.2343 0.03043 0.02301 0.0192 0.2635 1.0000
11.500 1.2268 0.03100 0.02365 0.0242 0.2577 1.0000
11.750 1.2192 0.03183 0.02455 0.0286 0.2517 1.0000
12.000 1.2114 0.03299 0.02580 0.0321 0.2448 1.0000
12.250 1.2070 0.03429 0.02718 0.0346 0.2380 1.0000
12.500 1.1995 0.03613 0.02913 0.0365 0.2304 1.0000
12.750 1.1926 0.03826 0.03135 0.0378 0.2231 1.0000
13.000 1.1856 0.04063 0.03378 0.0385 0.2153 1.0000
13.250 1.1745 0.04377 0.03702 0.0388 0.2077 1.0000
13.500 1.1697 0.04628 0.03953 0.0390 0.1999 1.0000
13.750 1.1534 0.05049 0.04388 0.0384 0.1925 1.0000
14.000 1.1471 0.05349 0.04688 0.0381 0.1849 1.0000
14.250 1.1318 0.05788 0.05138 0.0372 0.1775 1.0000
14.500 1.1231 0.06143 0.05495 0.0365 0.1701 1.0000
14.750 1.1119 0.06550 0.05908 0.0355 0.1627 1.0000
15.000 1.1028 0.06945 0.06307 0.0345 0.1556 1.0000
15.250 1.0963 0.07308 0.06672 0.0335 0.1482 1.0000
15.500 1.0864 0.07745 0.07117 0.0321 0.1416 1.0000
15.750 1.0837 0.08070 0.07440 0.0312 0.1348 1.0000
16.000 1.0728 0.08549 0.07930 0.0295 0.1283 1.0000
16.250 1.0722 0.08849 0.08228 0.0286 0.1218 1.0000
16.500 1.0621 0.09337 0.08726 0.0267 0.1158 1.0000
16.750 1.0584 0.09711 0.09102 0.0253 0.1100 1.0000
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Polar data table (+)
Polar graphs
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