EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 50,000 Max Cl/Cd: 30.14 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e361-il-50000.txt Download as CSV file: xf-e361-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4377 0.10698 0.10025 0.0000 1.0000 0.3100
-9.000 -0.4328 0.10367 0.09700 0.0003 1.0000 0.3255
-8.750 -0.4279 0.10047 0.09385 0.0007 1.0000 0.3410
-8.500 -0.4218 0.09715 0.09059 0.0013 1.0000 0.3577
-8.250 -0.4157 0.09392 0.08742 0.0019 1.0000 0.3745
-8.000 -0.4094 0.09081 0.08438 0.0026 1.0000 0.3914
-7.000 -0.5730 0.06136 0.05470 -0.0239 1.0000 0.1571
-6.750 -0.5892 0.05616 0.04875 -0.0214 1.0000 0.1310
-6.500 -0.5773 0.05241 0.04498 -0.0197 1.0000 0.1258
-6.250 -0.5837 0.04957 0.04130 -0.0154 1.0000 0.1150
-6.000 -0.5751 0.04625 0.03795 -0.0130 1.0000 0.1133
-5.750 -0.5696 0.04363 0.03517 -0.0100 1.0000 0.1110
-5.500 -0.5652 0.04129 0.03255 -0.0067 1.0000 0.1086
-5.250 -0.5590 0.03911 0.03002 -0.0036 1.0000 0.1067
-5.000 -0.5501 0.03709 0.02766 -0.0007 1.0000 0.1065
-4.750 -0.5390 0.03535 0.02564 0.0018 1.0000 0.1087
-4.500 -0.5258 0.03382 0.02373 0.0041 1.0000 0.1123
-4.250 -0.5096 0.03226 0.02178 0.0062 1.0000 0.1157
-4.000 -0.4906 0.03053 0.02013 0.0074 1.0000 0.1233
-3.750 -0.4693 0.02914 0.01862 0.0086 1.0000 0.1339
-3.500 -0.0173 0.02411 0.01567 -0.0388 1.0000 1.0000
-3.250 -0.0180 0.02407 0.01560 -0.0365 1.0000 1.0000
-3.000 -0.0314 0.02447 0.01600 -0.0323 1.0000 1.0000
-2.750 -0.0503 0.02502 0.01652 -0.0275 1.0000 1.0000
-2.500 -0.0655 0.02543 0.01689 -0.0232 1.0000 1.0000
-2.250 -0.0768 0.02574 0.01712 -0.0193 1.0000 1.0000
-2.000 -0.0854 0.02597 0.01727 -0.0158 1.0000 1.0000
-1.750 -0.0919 0.02616 0.01736 -0.0124 1.0000 1.0000
-1.500 -0.0898 0.02632 0.01741 -0.0104 0.9985 1.0000
-1.250 -0.0452 0.02667 0.01752 -0.0158 0.9866 1.0000
-1.000 -0.0048 0.02702 0.01768 -0.0202 0.9750 1.0000
-0.750 0.0297 0.02737 0.01787 -0.0234 0.9639 1.0000
-0.500 0.0637 0.02777 0.01813 -0.0263 0.9531 1.0000
-0.250 0.1042 0.02824 0.01847 -0.0303 0.9433 1.0000
0.000 0.1258 0.02865 0.01879 -0.0308 0.9318 1.0000
0.250 0.1501 0.02915 0.01921 -0.0318 0.9216 1.0000
0.500 0.1923 0.02969 0.01967 -0.0356 0.9120 1.0000
0.750 0.2008 0.03024 0.02017 -0.0337 0.9008 1.0000
1.000 0.2216 0.03085 0.02074 -0.0338 0.8903 1.0000
1.250 0.2635 0.03146 0.02133 -0.0372 0.8802 1.0000
1.500 0.2659 0.03214 0.02197 -0.0341 0.8685 1.0000
1.750 0.2825 0.03284 0.02265 -0.0333 0.8571 1.0000
2.000 0.3155 0.03353 0.02334 -0.0349 0.8455 1.0000
2.250 0.3485 0.03417 0.02400 -0.0364 0.8328 1.0000
2.500 0.3576 0.03493 0.02476 -0.0341 0.8191 1.0000
2.750 0.3769 0.03566 0.02550 -0.0332 0.8047 1.0000
3.000 0.4039 0.03631 0.02620 -0.0333 0.7892 1.0000
3.250 0.4418 0.03676 0.02673 -0.0347 0.7719 1.0000
3.500 0.4931 0.03670 0.02680 -0.0372 0.7530 1.0000
3.750 0.5340 0.03653 0.02675 -0.0377 0.7333 1.0000
4.000 0.5481 0.03694 0.02721 -0.0348 0.7128 1.0000
4.250 0.5838 0.03647 0.02684 -0.0338 0.6910 1.0000
4.500 0.6359 0.03492 0.02546 -0.0334 0.6700 1.0000
4.750 0.6470 0.03512 0.02572 -0.0297 0.6466 1.0000
5.000 0.6840 0.03376 0.02446 -0.0274 0.6239 1.0000
5.250 0.7065 0.03307 0.02386 -0.0241 0.5983 1.0000
5.500 0.7442 0.03119 0.02200 -0.0214 0.5725 1.0000
5.750 0.7696 0.02996 0.02076 -0.0180 0.5407 1.0000
6.000 0.7871 0.02929 0.02011 -0.0142 0.5034 1.0000
6.250 0.8127 0.02808 0.01869 -0.0109 0.4638 1.0000
6.500 0.8284 0.02800 0.01845 -0.0075 0.4236 1.0000
6.750 0.8475 0.02812 0.01828 -0.0048 0.3886 1.0000
7.000 0.8642 0.02887 0.01882 -0.0024 0.3592 1.0000
7.250 0.8814 0.02994 0.01976 -0.0004 0.3350 1.0000
7.500 0.8998 0.03110 0.02080 0.0013 0.3145 1.0000
7.750 0.9195 0.03246 0.02209 0.0027 0.2977 1.0000
8.000 0.9376 0.03397 0.02362 0.0042 0.2828 1.0000
8.250 0.9533 0.03567 0.02543 0.0058 0.2700 1.0000
8.500 0.9701 0.03756 0.02742 0.0071 0.2594 1.0000
8.750 0.9917 0.03934 0.02915 0.0080 0.2484 1.0000
9.000 0.9975 0.04159 0.03179 0.0103 0.2400 1.0000
9.250 1.0152 0.04384 0.03408 0.0114 0.2322 1.0000
9.500 1.0136 0.04667 0.03734 0.0140 0.2265 1.0000
9.750 1.0360 0.04877 0.03938 0.0146 0.2180 1.0000
10.000 1.0218 0.05232 0.04342 0.0178 0.2149 1.0000
10.250 1.0052 0.05624 0.04768 0.0205 0.2126 1.0000
10.500 0.9794 0.06071 0.05239 0.0231 0.2116 1.0000
10.750 0.9318 0.06641 0.05823 0.0256 0.2137 1.0000
11.000 0.8761 0.07461 0.06645 0.0245 0.2167 1.0000
11.250 0.8366 0.08396 0.07579 0.0209 0.2188 1.0000
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Polar data table (+)
Polar graphs
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