EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 200,000 Max Cl/Cd: 52.51 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e360-il-200000-n5.txt Download as CSV file: xf-e360-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5363 0.08444 0.08075 -0.0299 1.0000 0.0130
-10.250 -0.5581 0.07324 0.06956 -0.0385 1.0000 0.0127
-10.000 -0.5830 0.06549 0.06170 -0.0433 1.0000 0.0124
-9.750 -0.6087 0.05983 0.05590 -0.0445 1.0000 0.0121
-9.500 -0.6379 0.05477 0.05066 -0.0427 1.0000 0.0119
-9.250 -0.6648 0.05046 0.04615 -0.0385 1.0000 0.0118
-9.000 -0.7088 0.04187 0.03681 -0.0320 1.0000 0.0111
-8.750 -0.7161 0.03827 0.03277 -0.0279 1.0000 0.0110
-8.500 -0.7158 0.03547 0.02960 -0.0244 1.0000 0.0109
-8.250 -0.7111 0.03314 0.02698 -0.0214 1.0000 0.0109
-8.000 -0.7035 0.03099 0.02454 -0.0185 1.0000 0.0110
-7.750 -0.6935 0.02915 0.02246 -0.0159 1.0000 0.0110
-7.500 -0.6819 0.02751 0.02061 -0.0134 1.0000 0.0111
-7.250 -0.6582 0.02584 0.01874 -0.0133 0.9958 0.0114
-7.000 -0.6266 0.02411 0.01679 -0.0147 0.9875 0.0116
-6.750 -0.5953 0.02264 0.01514 -0.0158 0.9771 0.0120
-6.500 -0.5637 0.02131 0.01364 -0.0168 0.9653 0.0124
-6.250 -0.5317 0.02006 0.01226 -0.0179 0.9518 0.0129
-6.000 -0.4984 0.01891 0.01097 -0.0192 0.9374 0.0135
-5.750 -0.4645 0.01786 0.00984 -0.0207 0.9221 0.0145
-5.500 -0.4302 0.01712 0.00905 -0.0223 0.9054 0.0159
-5.250 -0.3986 0.01642 0.00826 -0.0232 0.8874 0.0183
-5.000 -0.3699 0.01580 0.00754 -0.0234 0.8686 0.0204
-4.750 -0.3441 0.01521 0.00685 -0.0230 0.8506 0.0230
-4.500 -0.3198 0.01473 0.00630 -0.0223 0.8335 0.0286
-4.000 -0.2737 0.01382 0.00536 -0.0203 0.8030 0.0542
-3.750 -0.2513 0.01338 0.00499 -0.0193 0.7892 0.0814
-3.500 -0.2303 0.01282 0.00464 -0.0182 0.7766 0.1344
-3.250 -0.2125 0.01202 0.00428 -0.0166 0.7650 0.2432
-3.000 -0.1988 0.01104 0.00393 -0.0143 0.7541 0.4025
-2.750 -0.1866 0.01017 0.00380 -0.0112 0.7432 0.5779
-2.500 -0.1657 0.00995 0.00389 -0.0092 0.7337 0.6791
-2.250 -0.1411 0.00996 0.00394 -0.0080 0.7243 0.7281
-2.000 -0.1160 0.01003 0.00398 -0.0069 0.7153 0.7604
-1.750 -0.0912 0.01015 0.00406 -0.0057 0.7070 0.7898
-1.500 -0.0672 0.01030 0.00418 -0.0043 0.6984 0.8171
-1.250 -0.0415 0.01046 0.00428 -0.0032 0.6908 0.8347
-1.000 -0.0158 0.01056 0.00431 -0.0024 0.6828 0.8474
-0.750 0.0122 0.01065 0.00432 -0.0020 0.6755 0.8550
-0.500 0.0376 0.01068 0.00428 -0.0014 0.6681 0.8636
-0.250 0.0661 0.01073 0.00426 -0.0013 0.6609 0.8685
0.000 0.0938 0.01078 0.00423 -0.0012 0.6540 0.8738
0.250 0.1189 0.01079 0.00418 -0.0006 0.6468 0.8804
0.500 0.1482 0.01085 0.00418 -0.0007 0.6405 0.8841
0.750 0.1765 0.01089 0.00419 -0.0007 0.6330 0.8886
1.000 0.2027 0.01093 0.00417 -0.0003 0.6265 0.8944
1.250 0.2306 0.01097 0.00419 -0.0003 0.6181 0.8987
1.500 0.2596 0.01103 0.00419 -0.0004 0.6092 0.9027
1.750 0.2866 0.01106 0.00419 -0.0002 0.5974 0.9078
2.000 0.3123 0.01108 0.00417 0.0003 0.5842 0.9132
2.250 0.3420 0.01114 0.00418 0.0000 0.5700 0.9167
2.500 0.3706 0.01119 0.00420 -0.0001 0.5566 0.9211
2.750 0.3960 0.01124 0.00422 0.0004 0.5443 0.9270
3.000 0.4262 0.01132 0.00427 -0.0001 0.5315 0.9305
3.250 0.4568 0.01140 0.00434 -0.0007 0.5173 0.9341
3.500 0.4854 0.01148 0.00441 -0.0009 0.5022 0.9389
3.750 0.5122 0.01157 0.00449 -0.0007 0.4856 0.9442
4.000 0.5441 0.01169 0.00459 -0.0017 0.4644 0.9473
4.250 0.5738 0.01186 0.00468 -0.0022 0.4375 0.9513
4.500 0.5998 0.01206 0.00480 -0.0020 0.4057 0.9572
4.750 0.6287 0.01240 0.00497 -0.0026 0.3629 0.9610
5.000 0.6568 0.01288 0.00522 -0.0032 0.3124 0.9651
5.250 0.6821 0.01342 0.00556 -0.0033 0.2694 0.9710
5.500 0.7114 0.01395 0.00593 -0.0042 0.2351 0.9749
5.750 0.7407 0.01447 0.00633 -0.0052 0.2072 0.9791
6.000 0.7682 0.01495 0.00674 -0.0057 0.1860 0.9845
6.250 0.7993 0.01543 0.00716 -0.0070 0.1694 0.9883
6.500 0.8289 0.01589 0.00759 -0.0080 0.1567 0.9931
6.750 0.8591 0.01636 0.00806 -0.0092 0.1457 0.9977
7.250 0.8918 0.01715 0.00886 -0.0058 0.1322 1.0000
7.500 0.9035 0.01754 0.00926 -0.0031 0.1265 1.0000
7.750 0.9158 0.01798 0.00969 -0.0006 0.1218 1.0000
8.000 0.9301 0.01837 0.01012 0.0015 0.1167 1.0000
8.250 0.9434 0.01885 0.01060 0.0038 0.1122 1.0000
8.500 0.9572 0.01936 0.01113 0.0059 0.1082 1.0000
8.750 0.9730 0.01981 0.01165 0.0078 0.1040 1.0000
9.000 0.9876 0.02034 0.01220 0.0096 0.1002 1.0000
9.250 0.9999 0.02101 0.01285 0.0118 0.0967 1.0000
9.500 1.0159 0.02149 0.01344 0.0134 0.0932 1.0000
9.750 1.0293 0.02203 0.01406 0.0154 0.0899 1.0000
10.000 1.0407 0.02266 0.01472 0.0176 0.0868 1.0000
10.250 1.0501 0.02346 0.01551 0.0199 0.0841 1.0000
10.500 1.0641 0.02409 0.01626 0.0216 0.0813 1.0000
10.750 1.0770 0.02479 0.01706 0.0232 0.0782 1.0000
11.000 1.0884 0.02559 0.01792 0.0248 0.0754 1.0000
11.250 1.0973 0.02661 0.01895 0.0265 0.0730 1.0000
11.500 1.1094 0.02752 0.01997 0.0278 0.0706 1.0000
11.750 1.1210 0.02847 0.02104 0.0290 0.0680 1.0000
12.000 1.1313 0.02952 0.02218 0.0301 0.0656 1.0000
12.250 1.1395 0.03075 0.02347 0.0312 0.0634 1.0000
12.500 1.1470 0.03215 0.02491 0.0322 0.0615 1.0000
12.750 1.1571 0.03340 0.02632 0.0330 0.0594 1.0000
13.000 1.1658 0.03478 0.02783 0.0337 0.0571 1.0000
13.250 1.1729 0.03631 0.02944 0.0343 0.0552 1.0000
13.500 1.1777 0.03807 0.03125 0.0348 0.0534 1.0000
13.750 1.1826 0.03994 0.03320 0.0352 0.0517 1.0000
14.000 1.1888 0.04175 0.03519 0.0355 0.0499 1.0000
14.250 1.1933 0.04376 0.03733 0.0356 0.0481 1.0000
14.500 1.1965 0.04594 0.03962 0.0356 0.0466 1.0000
14.750 1.1975 0.04836 0.04212 0.0353 0.0452 1.0000
15.000 1.1963 0.05111 0.04491 0.0350 0.0440 1.0000
15.250 1.1975 0.05375 0.04774 0.0346 0.0427 1.0000
15.500 1.1971 0.05664 0.05080 0.0340 0.0413 1.0000
15.750 1.1950 0.05981 0.05411 0.0331 0.0401 1.0000
16.000 1.1917 0.06325 0.05768 0.0319 0.0390 1.0000
16.250 1.1871 0.06700 0.06153 0.0305 0.0380 1.0000
16.500 1.1811 0.07106 0.06569 0.0289 0.0372 1.0000
16.750 1.1740 0.07542 0.07014 0.0270 0.0364 1.0000
17.000 1.1656 0.08024 0.07516 0.0248 0.0356 1.0000
17.250 1.1554 0.08554 0.08064 0.0223 0.0349 1.0000
17.500 1.1432 0.09137 0.08665 0.0193 0.0342 1.0000
17.750 1.1290 0.09774 0.09317 0.0159 0.0335 1.0000
18.000 1.1136 0.10458 0.10018 0.0121 0.0330 1.0000
18.250 1.0959 0.11213 0.10787 0.0078 0.0324 1.0000
18.500 1.0749 0.12050 0.11639 0.0030 0.0322 1.0000
18.750 1.0493 0.13023 0.12627 -0.0027 0.0319 1.0000
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