EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 200,000 Max Cl/Cd: 49.29 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e472-il-200000-n5.txt Download as CSV file: xf-e472-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 472 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9728 0.11222 0.10772 -0.0069 1.0000 0.0540
-16.500 -1.0422 0.09579 0.09108 -0.0164 1.0000 0.0548
-16.250 -1.0874 0.08473 0.07987 -0.0227 1.0000 0.0553
-16.000 -1.1263 0.07501 0.06998 -0.0283 1.0000 0.0558
-15.750 -1.1583 0.06652 0.06131 -0.0333 1.0000 0.0563
-15.500 -1.1843 0.05902 0.05363 -0.0379 1.0000 0.0568
-15.250 -1.2053 0.05245 0.04690 -0.0420 1.0000 0.0576
-15.000 -1.2212 0.04702 0.04136 -0.0453 1.0000 0.0584
-14.750 -1.2330 0.04271 0.03691 -0.0475 1.0000 0.0593
-14.500 -1.2409 0.03943 0.03351 -0.0483 1.0000 0.0607
-14.250 -1.2453 0.03693 0.03087 -0.0481 1.0000 0.0623
-14.000 -1.2471 0.03496 0.02874 -0.0470 1.0000 0.0640
-13.750 -1.2459 0.03336 0.02694 -0.0453 1.0000 0.0658
-13.500 -1.2464 0.03196 0.02552 -0.0430 1.0000 0.0674
-13.250 -1.2437 0.03085 0.02435 -0.0404 1.0000 0.0693
-13.000 -1.2393 0.02990 0.02330 -0.0377 1.0000 0.0714
-12.750 -1.2331 0.02902 0.02228 -0.0349 1.0000 0.0738
-12.500 -1.2243 0.02814 0.02129 -0.0324 1.0000 0.0762
-12.250 -1.2140 0.02738 0.02052 -0.0301 1.0000 0.0786
-12.000 -1.2010 0.02669 0.01974 -0.0281 1.0000 0.0814
-11.750 -1.1865 0.02600 0.01890 -0.0262 1.0000 0.0843
-11.500 -1.1719 0.02528 0.01809 -0.0243 1.0000 0.0868
-11.250 -1.1569 0.02466 0.01747 -0.0224 1.0000 0.0894
-11.000 -1.1401 0.02410 0.01683 -0.0207 1.0000 0.0921
-10.750 -1.1223 0.02352 0.01611 -0.0191 1.0000 0.0952
-10.500 -1.1044 0.02292 0.01541 -0.0175 1.0000 0.0978
-10.250 -1.0867 0.02239 0.01488 -0.0158 1.0000 0.1005
-10.000 -1.0676 0.02191 0.01435 -0.0143 1.0000 0.1034
-9.750 -1.0479 0.02143 0.01375 -0.0129 1.0000 0.1065
-9.500 -1.0277 0.02095 0.01314 -0.0115 1.0000 0.1094
-9.250 -1.0084 0.02046 0.01267 -0.0100 1.0000 0.1122
-9.000 -0.9880 0.02006 0.01224 -0.0086 1.0000 0.1152
-8.750 -0.9669 0.01966 0.01176 -0.0073 1.0000 0.1186
-8.500 -0.9454 0.01927 0.01123 -0.0060 1.0000 0.1217
-8.250 -0.9248 0.01882 0.01081 -0.0046 1.0000 0.1246
-8.000 -0.9035 0.01847 0.01045 -0.0033 1.0000 0.1278
-7.750 -0.8816 0.01814 0.01005 -0.0020 1.0000 0.1313
-7.500 -0.8593 0.01780 0.00961 -0.0008 1.0000 0.1347
-7.250 -0.8377 0.01741 0.00923 0.0005 1.0000 0.1377
-7.000 -0.8158 0.01710 0.00892 0.0017 1.0000 0.1410
-6.750 -0.7934 0.01681 0.00859 0.0029 1.0000 0.1446
-6.500 -0.7707 0.01652 0.00823 0.0041 1.0000 0.1482
-6.250 -0.7484 0.01619 0.00788 0.0053 1.0000 0.1513
-6.000 -0.7262 0.01589 0.00761 0.0066 1.0000 0.1548
-5.750 -0.7035 0.01564 0.00735 0.0078 1.0000 0.1585
-5.500 -0.6807 0.01539 0.00705 0.0089 1.0000 0.1622
-5.250 -0.6579 0.01512 0.00676 0.0101 1.0000 0.1656
-5.000 -0.6357 0.01484 0.00653 0.0113 1.0000 0.1692
-4.750 -0.6130 0.01462 0.00632 0.0125 1.0000 0.1732
-4.500 -0.5902 0.01441 0.00608 0.0137 1.0000 0.1771
-4.250 -0.5674 0.01420 0.00586 0.0149 1.0000 0.1806
-4.000 -0.5453 0.01395 0.00568 0.0162 1.0000 0.1846
-3.750 -0.5177 0.01376 0.00552 0.0163 0.9985 0.1894
-3.500 -0.4704 0.01360 0.00534 0.0124 0.9897 0.1952
-3.250 -0.4286 0.01331 0.00515 0.0096 0.9801 0.2007
-3.000 -0.3930 0.01306 0.00494 0.0083 0.9669 0.2070
-2.750 -0.3626 0.01281 0.00471 0.0081 0.9488 0.2126
-2.500 -0.3274 0.01250 0.00448 0.0069 0.9279 0.2186
-2.250 -0.2804 0.01225 0.00425 0.0034 0.8989 0.2272
-2.000 -0.2041 0.01190 0.00388 -0.0062 0.8270 0.2395
-1.750 -0.1615 0.01194 0.00361 -0.0086 0.7245 0.2488
-1.500 -0.1378 0.01210 0.00349 -0.0073 0.6430 0.2582
-1.250 -0.1160 0.01226 0.00340 -0.0057 0.5717 0.2683
-1.000 -0.0937 0.01240 0.00333 -0.0043 0.5102 0.2800
-0.750 -0.0709 0.01250 0.00327 -0.0031 0.4584 0.2936
-0.500 -0.0475 0.01256 0.00324 -0.0020 0.4171 0.3092
-0.250 -0.0237 0.01260 0.00322 -0.0010 0.3826 0.3289
0.000 0.0000 0.01260 0.00321 0.0000 0.3533 0.3533
0.250 0.0237 0.01260 0.00322 0.0010 0.3290 0.3826
0.500 0.0475 0.01256 0.00324 0.0020 0.3092 0.4171
0.750 0.0709 0.01250 0.00327 0.0031 0.2935 0.4583
1.000 0.0937 0.01240 0.00333 0.0043 0.2801 0.5098
1.250 0.1160 0.01226 0.00340 0.0057 0.2683 0.5720
1.500 0.1378 0.01210 0.00349 0.0073 0.2582 0.6429
1.750 0.1615 0.01194 0.00361 0.0086 0.2489 0.7247
2.000 0.2046 0.01190 0.00388 0.0061 0.2394 0.8280
2.250 0.2805 0.01225 0.00425 -0.0034 0.2271 0.8990
2.500 0.3273 0.01250 0.00448 -0.0069 0.2187 0.9279
2.750 0.3626 0.01281 0.00471 -0.0081 0.2126 0.9486
3.000 0.3930 0.01306 0.00494 -0.0083 0.2070 0.9672
3.250 0.4287 0.01331 0.00515 -0.0097 0.2008 0.9803
3.500 0.4701 0.01359 0.00534 -0.0124 0.1953 0.9896
3.750 0.5179 0.01376 0.00552 -0.0163 0.1893 0.9986
4.000 0.5453 0.01395 0.00568 -0.0162 0.1847 1.0000
4.250 0.5674 0.01420 0.00586 -0.0149 0.1807 1.0000
4.500 0.5902 0.01441 0.00608 -0.0137 0.1771 1.0000
4.750 0.6130 0.01461 0.00632 -0.0125 0.1732 1.0000
5.000 0.6357 0.01484 0.00653 -0.0113 0.1693 1.0000
5.250 0.6579 0.01512 0.00676 -0.0101 0.1656 1.0000
5.500 0.6807 0.01539 0.00705 -0.0089 0.1622 1.0000
5.750 0.7035 0.01563 0.00734 -0.0078 0.1585 1.0000
6.000 0.7262 0.01589 0.00761 -0.0066 0.1548 1.0000
6.250 0.7484 0.01618 0.00788 -0.0053 0.1513 1.0000
6.500 0.7707 0.01652 0.00823 -0.0041 0.1481 1.0000
6.750 0.7934 0.01681 0.00859 -0.0029 0.1447 1.0000
7.000 0.8158 0.01710 0.00892 -0.0017 0.1411 1.0000
7.250 0.8377 0.01741 0.00923 -0.0005 0.1377 1.0000
7.500 0.8593 0.01780 0.00961 0.0008 0.1347 1.0000
7.750 0.8816 0.01814 0.01005 0.0020 0.1314 1.0000
8.000 0.9035 0.01847 0.01045 0.0033 0.1278 1.0000
8.250 0.9248 0.01882 0.01081 0.0046 0.1246 1.0000
8.500 0.9454 0.01926 0.01123 0.0060 0.1217 1.0000
8.750 0.9670 0.01966 0.01175 0.0073 0.1185 1.0000
9.000 0.9880 0.02005 0.01224 0.0086 0.1152 1.0000
9.250 1.0084 0.02046 0.01268 0.0100 0.1122 1.0000
9.500 1.0277 0.02095 0.01314 0.0115 0.1095 1.0000
9.750 1.0479 0.02143 0.01375 0.0129 0.1065 1.0000
10.000 1.0677 0.02191 0.01435 0.0143 0.1034 1.0000
10.250 1.0867 0.02238 0.01488 0.0158 0.1005 1.0000
10.500 1.1044 0.02292 0.01541 0.0175 0.0979 1.0000
10.750 1.1224 0.02352 0.01611 0.0191 0.0951 1.0000
11.000 1.1401 0.02410 0.01683 0.0207 0.0921 1.0000
11.250 1.1569 0.02466 0.01747 0.0224 0.0894 1.0000
11.500 1.1720 0.02528 0.01809 0.0243 0.0868 1.0000
11.750 1.1866 0.02600 0.01890 0.0262 0.0843 1.0000
12.000 1.2012 0.02669 0.01974 0.0281 0.0814 1.0000
12.250 1.2142 0.02737 0.02051 0.0301 0.0786 1.0000
12.500 1.2245 0.02814 0.02129 0.0324 0.0762 1.0000
12.750 1.2334 0.02901 0.02228 0.0348 0.0738 1.0000
13.000 1.2398 0.02989 0.02329 0.0376 0.0714 1.0000
13.250 1.2441 0.03084 0.02434 0.0404 0.0692 1.0000
13.500 1.2468 0.03195 0.02551 0.0429 0.0674 1.0000
13.750 1.2465 0.03334 0.02693 0.0452 0.0658 1.0000
14.000 1.2478 0.03494 0.02872 0.0469 0.0639 1.0000
14.250 1.2461 0.03692 0.03086 0.0480 0.0622 1.0000
14.500 1.2418 0.03940 0.03348 0.0483 0.0607 1.0000
14.750 1.2340 0.04267 0.03687 0.0474 0.0594 1.0000
15.000 1.2223 0.04698 0.04131 0.0452 0.0583 1.0000
15.250 1.2066 0.05239 0.04684 0.0419 0.0575 1.0000
15.500 1.1862 0.05888 0.05348 0.0378 0.0568 1.0000
15.750 1.1592 0.06659 0.06138 0.0331 0.0561 1.0000
16.000 1.1269 0.07514 0.07011 0.0280 0.0557 1.0000
16.250 1.0885 0.08479 0.07993 0.0225 0.0552 1.0000
16.500 1.0444 0.09565 0.09094 0.0163 0.0547 1.0000
16.750 0.9752 0.11206 0.10756 0.0068 0.0539 1.0000
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Polar data table (+)
Polar graphs
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