EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 100,000 Max Cl/Cd: 47.63 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e360-il-100000.txt Download as CSV file: xf-e360-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4752 0.10774 0.10269 -0.0178 1.0000 0.1064
-10.000 -0.4942 0.10339 0.09844 -0.0233 1.0000 0.1109
-9.750 -0.5365 0.09745 0.09261 -0.0332 1.0000 0.1119
-9.500 -0.4864 0.09512 0.09025 -0.0239 1.0000 0.1163
-9.250 -0.4842 0.09161 0.08679 -0.0246 1.0000 0.1209
-9.000 -0.5142 0.08584 0.08112 -0.0317 1.0000 0.1251
-8.750 -0.5648 0.08235 0.07762 -0.0338 1.0000 0.1262
-8.500 -0.5392 0.07730 0.07268 -0.0332 1.0000 0.1302
-8.250 -0.5352 0.07447 0.06988 -0.0319 1.0000 0.1347
-8.000 -0.5631 0.07147 0.06682 -0.0310 1.0000 0.1393
-7.750 -0.5816 0.06778 0.06310 -0.0296 1.0000 0.1444
-7.500 -0.5690 0.06487 0.06026 -0.0280 1.0000 0.1498
-6.500 -0.6038 0.04404 0.03752 -0.0151 1.0000 0.0686
-6.250 -0.6049 0.04042 0.03321 -0.0098 1.0000 0.0582
-6.000 -0.6010 0.03789 0.03054 -0.0065 1.0000 0.0572
-5.750 -0.5977 0.03592 0.02831 -0.0029 1.0000 0.0570
-5.500 -0.5921 0.03405 0.02622 0.0003 1.0000 0.0565
-5.250 -0.5844 0.03228 0.02416 0.0033 1.0000 0.0564
-5.000 -0.5609 0.03002 0.02156 0.0037 0.9971 0.0556
-4.750 -0.5170 0.02752 0.01865 0.0010 0.9896 0.0558
-4.500 -0.4715 0.02575 0.01647 -0.0018 0.9820 0.0588
-4.250 -0.4283 0.02377 0.01461 -0.0050 0.9744 0.0670
-4.000 -0.3883 0.02207 0.01299 -0.0072 0.9654 0.0780
-3.750 -0.3498 0.02045 0.01155 -0.0094 0.9570 0.1038
-3.500 -0.3208 0.01833 0.01018 -0.0101 0.9469 0.1962
-3.250 -0.3188 0.01620 0.01093 -0.0030 0.9359 0.7509
-3.000 -0.2718 0.01775 0.01235 -0.0019 0.9311 0.8429
-2.750 -0.1878 0.01955 0.01380 -0.0078 0.9319 0.8852
-2.500 -0.0598 0.02088 0.01472 -0.0224 0.9403 0.9262
-2.250 0.0212 0.02062 0.01421 -0.0320 0.9368 0.9452
-2.000 0.0895 0.02011 0.01351 -0.0401 0.9308 0.9576
-1.750 0.1513 0.01945 0.01269 -0.0472 0.9201 0.9666
-1.500 0.2054 0.01890 0.01200 -0.0530 0.9090 0.9751
-1.250 0.2563 0.01838 0.01135 -0.0580 0.8971 0.9832
-1.000 0.3031 0.01783 0.01070 -0.0624 0.8835 0.9905
-0.750 0.3453 0.01738 0.01017 -0.0659 0.8696 0.9978
-0.500 0.3726 0.01725 0.00997 -0.0665 0.8557 1.0000
-0.250 0.3926 0.01728 0.00994 -0.0656 0.8424 1.0000
0.000 0.4122 0.01733 0.00994 -0.0645 0.8302 1.0000
0.250 0.4318 0.01739 0.00994 -0.0633 0.8187 1.0000
0.500 0.4503 0.01751 0.01004 -0.0621 0.8063 1.0000
0.750 0.4688 0.01762 0.01013 -0.0608 0.7945 1.0000
1.000 0.4878 0.01769 0.01017 -0.0593 0.7834 1.0000
1.250 0.5063 0.01774 0.01018 -0.0576 0.7708 1.0000
1.500 0.5239 0.01780 0.01022 -0.0559 0.7568 1.0000
1.750 0.5415 0.01782 0.01023 -0.0539 0.7424 1.0000
2.000 0.5593 0.01781 0.01019 -0.0519 0.7277 1.0000
2.250 0.5775 0.01779 0.01014 -0.0500 0.7133 1.0000
2.500 0.5960 0.01776 0.01010 -0.0481 0.6995 1.0000
2.750 0.6151 0.01772 0.01005 -0.0463 0.6861 1.0000
3.000 0.6347 0.01766 0.00994 -0.0445 0.6729 1.0000
3.250 0.6536 0.01763 0.00992 -0.0427 0.6586 1.0000
3.500 0.6723 0.01759 0.00989 -0.0409 0.6436 1.0000
3.750 0.6910 0.01754 0.00987 -0.0390 0.6283 1.0000
4.000 0.7098 0.01747 0.00982 -0.0371 0.6124 1.0000
4.250 0.7285 0.01737 0.00970 -0.0351 0.5954 1.0000
4.500 0.7464 0.01727 0.00963 -0.0330 0.5765 1.0000
4.750 0.7629 0.01719 0.00960 -0.0307 0.5545 1.0000
5.000 0.7802 0.01703 0.00940 -0.0283 0.5310 1.0000
5.250 0.7948 0.01695 0.00933 -0.0256 0.5006 1.0000
5.500 0.8073 0.01695 0.00930 -0.0226 0.4593 1.0000
5.750 0.8170 0.01716 0.00927 -0.0191 0.4054 1.0000
6.000 0.8235 0.01780 0.00951 -0.0153 0.3492 1.0000
6.250 0.8303 0.01867 0.01003 -0.0118 0.3074 1.0000
6.500 0.8392 0.01955 0.01065 -0.0086 0.2790 1.0000
6.750 0.8502 0.02044 0.01132 -0.0059 0.2580 1.0000
7.000 0.8640 0.02136 0.01203 -0.0037 0.2412 1.0000
7.250 0.8795 0.02221 0.01281 -0.0017 0.2271 1.0000
7.500 0.8958 0.02306 0.01364 0.0001 0.2146 1.0000
7.750 0.9132 0.02398 0.01456 0.0017 0.2038 1.0000
8.000 0.9334 0.02506 0.01551 0.0028 0.1946 1.0000
8.250 0.9510 0.02595 0.01650 0.0043 0.1857 1.0000
8.500 0.9712 0.02710 0.01764 0.0053 0.1777 1.0000
8.750 0.9904 0.02813 0.01874 0.0065 0.1702 1.0000
9.000 1.0110 0.02947 0.02011 0.0074 0.1634 1.0000
9.250 1.0283 0.03055 0.02134 0.0088 0.1566 1.0000
9.500 1.0509 0.03216 0.02292 0.0092 0.1508 1.0000
9.750 1.0648 0.03345 0.02453 0.0110 0.1453 1.0000
10.000 1.0843 0.03474 0.02583 0.0119 0.1396 1.0000
10.250 1.0990 0.03665 0.02795 0.0133 0.1351 1.0000
10.500 1.1099 0.03833 0.02995 0.0152 0.1307 1.0000
10.750 1.1275 0.03978 0.03146 0.0162 0.1260 1.0000
11.000 1.1392 0.04211 0.03397 0.0175 0.1221 1.0000
11.250 1.1388 0.04429 0.03658 0.0205 0.1191 1.0000
11.500 1.1426 0.04641 0.03897 0.0227 0.1158 1.0000
11.750 1.1610 0.04798 0.04051 0.0232 0.1117 1.0000
12.000 1.1637 0.05103 0.04374 0.0249 0.1091 1.0000
12.250 1.1455 0.05379 0.04691 0.0288 0.1078 1.0000
12.500 1.1232 0.05671 0.05013 0.0328 0.1071 1.0000
12.750 1.0968 0.06016 0.05384 0.0356 0.1066 1.0000
13.000 1.0660 0.06448 0.05840 0.0370 0.1065 1.0000
13.250 1.0305 0.06994 0.06407 0.0367 0.1068 1.0000
13.500 0.9903 0.07700 0.07131 0.0345 0.1077 1.0000
13.750 0.9468 0.08590 0.08033 0.0305 0.1087 1.0000
14.000 0.9074 0.09616 0.09065 0.0254 0.1096 1.0000
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Polar data table (+)
Polar graphs
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