EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.89 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e908-il-1000000-n5.txt Download as CSV file: xf-e908-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2776 0.07247 0.07070 -0.0962 0.9715 0.0021
-8.500 -0.2730 0.06638 0.06463 -0.1027 0.9700 0.0019
-8.250 -0.2773 0.06179 0.06005 -0.1057 0.9625 0.0019
-8.000 -0.2683 0.05426 0.05248 -0.1180 0.9588 0.0020
-7.750 -0.2620 0.04693 0.04504 -0.1257 0.9543 0.0019
-7.500 -0.2545 0.04061 0.03853 -0.1296 0.9499 0.0018
-7.250 -0.2423 0.03437 0.03199 -0.1326 0.9469 0.0016
-7.000 -0.2306 0.02926 0.02651 -0.1332 0.9435 0.0015
-6.750 -0.2232 0.02455 0.02140 -0.1314 0.9386 0.0013
-6.500 -0.2089 0.01961 0.01591 -0.1300 0.9355 0.0011
-6.250 -0.1911 0.01468 0.01030 -0.1283 0.9332 0.0009
-6.000 -0.1704 0.01231 0.00757 -0.1270 0.9312 0.0009
-5.750 -0.1495 0.01110 0.00616 -0.1258 0.9289 0.0009
-5.500 -0.1263 0.01027 0.00519 -0.1251 0.9269 0.0010
-5.250 -0.1014 0.00965 0.00447 -0.1248 0.9252 0.0012
-5.000 -0.0753 0.00918 0.00391 -0.1247 0.9235 0.0015
-4.750 -0.0480 0.00880 0.00346 -0.1249 0.9221 0.0019
-4.500 -0.0199 0.00850 0.00309 -0.1252 0.9208 0.0023
-4.250 0.0088 0.00831 0.00286 -0.1257 0.9193 0.0026
-3.750 0.0580 0.00769 0.00210 -0.1247 0.9137 0.0076
-3.500 0.0849 0.00745 0.00180 -0.1246 0.9111 0.0149
-3.250 0.1123 0.00704 0.00155 -0.1249 0.9086 0.0688
-2.750 0.1655 0.00654 0.00132 -0.1251 0.9042 0.1612
-2.500 0.1916 0.00639 0.00124 -0.1250 0.9018 0.1886
-2.250 0.2165 0.00590 0.00112 -0.1249 0.8996 0.3144
-2.000 0.2435 0.00568 0.00105 -0.1251 0.8976 0.3726
-1.750 0.2713 0.00546 0.00098 -0.1254 0.8958 0.4351
-1.500 0.2998 0.00525 0.00093 -0.1259 0.8941 0.4978
-1.250 0.3252 0.00506 0.00094 -0.1256 0.8918 0.5610
-1.000 0.3512 0.00498 0.00097 -0.1255 0.8892 0.6037
-0.750 0.3783 0.00495 0.00099 -0.1254 0.8867 0.6264
-0.500 0.4060 0.00493 0.00099 -0.1256 0.8844 0.6409
-0.250 0.4349 0.00492 0.00100 -0.1260 0.8822 0.6515
0.000 0.4627 0.00490 0.00103 -0.1261 0.8797 0.6651
0.250 0.4883 0.00488 0.00108 -0.1258 0.8765 0.6816
0.500 0.5149 0.00486 0.00113 -0.1257 0.8731 0.6969
0.750 0.5428 0.00485 0.00119 -0.1258 0.8700 0.7100
1.000 0.5706 0.00484 0.00123 -0.1259 0.8668 0.7210
1.500 0.5704 0.00609 0.00131 -0.1130 0.5940 0.7387
2.000 0.5653 0.00965 0.00251 -0.1014 0.0027 0.7540
2.250 0.5902 0.00978 0.00266 -0.1010 0.0019 0.7604
2.500 0.6150 0.00994 0.00285 -0.1005 0.0015 0.7675
2.750 0.6394 0.01013 0.00311 -0.0999 0.0014 0.7743
3.000 0.6633 0.01037 0.00350 -0.0991 0.0014 0.7821
3.250 0.6860 0.01071 0.00395 -0.0980 0.0014 0.7901
3.500 0.7072 0.01121 0.00459 -0.0965 0.0014 0.7994
4.250 0.7628 0.01390 0.00773 -0.0902 0.0018 0.8371
4.500 0.7887 0.01564 0.00965 -0.0894 0.0021 0.8523
5.500 0.9037 0.02367 0.01858 -0.0881 0.0036 1.0000
5.750 0.9238 0.02647 0.02169 -0.0863 0.0034 1.0000
6.000 0.9291 0.03327 0.02904 -0.0814 0.0030 1.0000
6.250 0.9416 0.03610 0.03213 -0.0783 0.0030 1.0000
6.500 0.9519 0.03905 0.03532 -0.0751 0.0030 1.0000
6.750 0.9604 0.04216 0.03867 -0.0716 0.0030 1.0000
7.000 0.9672 0.04533 0.04207 -0.0680 0.0030 1.0000
7.250 0.9721 0.04860 0.04555 -0.0644 0.0030 1.0000
7.500 0.9748 0.05199 0.04914 -0.0607 0.0030 1.0000
7.750 0.9755 0.05535 0.05270 -0.0570 0.0030 1.0000
8.000 0.9737 0.05879 0.05630 -0.0533 0.0030 1.0000
8.250 0.9691 0.06218 0.05985 -0.0495 0.0030 1.0000
8.500 0.9598 0.06531 0.06312 -0.0452 0.0030 1.0000
8.750 0.9462 0.06813 0.06605 -0.0406 0.0030 1.0000
9.000 0.9312 0.07119 0.06922 -0.0367 0.0030 1.0000
9.250 0.9155 0.07448 0.07261 -0.0338 0.0030 1.0000
9.500 0.8987 0.07827 0.07650 -0.0318 0.0030 1.0000
9.750 0.8817 0.08250 0.08082 -0.0310 0.0030 1.0000
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Polar data table (+)
Polar graphs
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