EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.47 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e297-il-1000000.txt Download as CSV file: xf-e297-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 297 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.9399 0.02809 0.02422 -0.0203 1.0000 0.0040
-9.750 -0.9272 0.02673 0.02270 -0.0187 1.0000 0.0039
-9.500 -0.9116 0.02561 0.02146 -0.0174 1.0000 0.0038
-9.250 -0.8878 0.02426 0.01997 -0.0179 0.9762 0.0037
-9.000 -0.8682 0.02159 0.01700 -0.0177 0.9479 0.0036
-8.500 -0.8438 0.01800 0.01287 -0.0130 0.9146 0.0035
-8.250 -0.8272 0.01680 0.01150 -0.0114 0.9054 0.0034
-8.000 -0.8102 0.01571 0.01025 -0.0097 0.8981 0.0035
-7.750 -0.7911 0.01481 0.00921 -0.0084 0.8915 0.0035
-7.500 -0.7713 0.01404 0.00830 -0.0072 0.8859 0.0035
-7.250 -0.7497 0.01334 0.00749 -0.0063 0.8808 0.0036
-7.000 -0.7274 0.01275 0.00681 -0.0055 0.8760 0.0036
-6.750 -0.7066 0.01196 0.00583 -0.0043 0.8717 0.0041
-6.500 -0.6833 0.01137 0.00516 -0.0036 0.8675 0.0056
-6.250 -0.6604 0.01078 0.00462 -0.0029 0.8635 0.0167
-6.000 -0.6353 0.01049 0.00432 -0.0026 0.8600 0.0228
-5.750 -0.6100 0.01018 0.00403 -0.0023 0.8565 0.0320
-5.500 -0.5850 0.00980 0.00374 -0.0020 0.8530 0.0485
-5.250 -0.5601 0.00942 0.00346 -0.0018 0.8496 0.0708
-4.750 -0.5116 0.00854 0.00292 -0.0011 0.8431 0.1514
-4.500 -0.4872 0.00806 0.00265 -0.0008 0.8398 0.2037
-4.250 -0.4621 0.00767 0.00243 -0.0005 0.8364 0.2522
-4.000 -0.4373 0.00727 0.00222 -0.0002 0.8333 0.3078
-3.750 -0.4128 0.00682 0.00202 0.0001 0.8302 0.3764
-3.500 -0.3885 0.00632 0.00183 0.0004 0.8268 0.4549
-3.250 -0.3629 0.00598 0.00166 0.0006 0.8233 0.5138
-3.000 -0.3369 0.00570 0.00154 0.0008 0.8201 0.5644
-2.750 -0.3105 0.00550 0.00146 0.0010 0.8168 0.6100
-2.500 -0.2834 0.00532 0.00141 0.0011 0.8133 0.6459
-2.250 -0.2558 0.00522 0.00137 0.0011 0.8096 0.6740
-2.000 -0.2278 0.00518 0.00134 0.0010 0.8061 0.6941
-1.750 -0.1996 0.00517 0.00133 0.0010 0.8024 0.7094
-1.500 -0.1711 0.00514 0.00131 0.0008 0.7981 0.7220
-1.250 -0.1427 0.00513 0.00130 0.0007 0.7939 0.7329
-0.750 -0.0856 0.00514 0.00130 0.0004 0.7854 0.7504
-0.500 -0.0571 0.00513 0.00130 0.0003 0.7805 0.7573
-0.250 -0.0286 0.00516 0.00128 0.0001 0.7755 0.7638
0.000 0.0000 0.00513 0.00129 0.0000 0.7695 0.7696
0.250 0.0286 0.00516 0.00128 -0.0001 0.7638 0.7755
0.500 0.0571 0.00513 0.00130 -0.0003 0.7573 0.7804
0.750 0.0856 0.00514 0.00130 -0.0004 0.7504 0.7854
1.250 0.1426 0.00513 0.00130 -0.0007 0.7330 0.7939
1.500 0.1711 0.00515 0.00131 -0.0008 0.7219 0.7981
1.750 0.1996 0.00517 0.00133 -0.0010 0.7094 0.8024
2.000 0.2278 0.00518 0.00134 -0.0010 0.6942 0.8061
2.250 0.2558 0.00522 0.00137 -0.0011 0.6739 0.8096
2.500 0.2834 0.00532 0.00141 -0.0010 0.6457 0.8133
2.750 0.3105 0.00550 0.00146 -0.0010 0.6099 0.8168
3.000 0.3369 0.00570 0.00154 -0.0008 0.5645 0.8201
3.250 0.3629 0.00598 0.00166 -0.0006 0.5139 0.8233
3.500 0.3885 0.00632 0.00183 -0.0004 0.4556 0.8268
3.750 0.4131 0.00681 0.00202 -0.0001 0.3787 0.8302
4.000 0.4374 0.00727 0.00222 0.0002 0.3084 0.8333
4.250 0.4622 0.00767 0.00243 0.0005 0.2521 0.8364
4.500 0.4873 0.00807 0.00265 0.0007 0.2036 0.8397
4.750 0.5119 0.00853 0.00291 0.0010 0.1527 0.8431
5.000 0.5361 0.00900 0.00318 0.0013 0.1064 0.8463
5.250 0.5604 0.00943 0.00346 0.0017 0.0708 0.8495
5.500 0.5853 0.00981 0.00374 0.0020 0.0478 0.8530
5.750 0.6103 0.01018 0.00403 0.0022 0.0317 0.8565
6.000 0.6357 0.01049 0.00432 0.0025 0.0230 0.8600
6.250 0.6609 0.01078 0.00462 0.0028 0.0167 0.8634
6.500 0.6839 0.01136 0.00515 0.0035 0.0060 0.8674
6.750 0.7072 0.01196 0.00582 0.0042 0.0041 0.8716
7.000 0.7281 0.01277 0.00681 0.0053 0.0036 0.8759
7.250 0.7505 0.01334 0.00749 0.0061 0.0036 0.8807
7.500 0.7722 0.01404 0.00829 0.0070 0.0035 0.8858
7.750 0.7919 0.01482 0.00922 0.0083 0.0035 0.8913
8.000 0.8110 0.01573 0.01026 0.0096 0.0034 0.8979
8.250 0.8282 0.01683 0.01153 0.0112 0.0034 0.9051
8.500 0.8443 0.01814 0.01302 0.0129 0.0035 0.9143
8.750 0.8591 0.01953 0.01462 0.0148 0.0035 0.9266
9.000 0.8693 0.02171 0.01713 0.0175 0.0036 0.9468
9.250 0.8891 0.02423 0.01993 0.0177 0.0037 0.9748
9.500 0.9136 0.02557 0.02141 0.0170 0.0038 1.0000
9.750 0.9290 0.02676 0.02273 0.0183 0.0039 1.0000
10.000 0.9420 0.02814 0.02427 0.0200 0.0040 1.0000
14.250 0.5320 0.14755 0.14618 -0.0172 0.0085 1.0000
14.500 0.5328 0.15102 0.14965 -0.0194 0.0083 1.0000
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Polar data table (+)
Polar graphs
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