E471 (6.25%) (e471-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 200,000 Max Cl/Cd: 105.46 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e471-il-200000.txt Download as CSV file: xf-e471-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3837 0.10615 0.10293 -0.0242 1.0000 0.0280
-7.500 -0.3937 0.10503 0.10187 -0.0222 1.0000 0.0281
-7.250 -0.4058 0.10401 0.10092 -0.0201 1.0000 0.0281
-7.000 -0.4097 0.10209 0.09904 -0.0198 1.0000 0.0282
-6.750 -0.4114 0.09988 0.09688 -0.0203 1.0000 0.0283
-6.500 -0.4109 0.09729 0.09432 -0.0215 1.0000 0.0283
-6.250 -0.4096 0.09102 0.08809 -0.0209 0.9986 0.0293
-6.000 -0.3944 0.08738 0.08444 -0.0205 0.9961 0.0307
-5.750 -0.3718 0.08344 0.08049 -0.0255 0.9920 0.0323
-5.500 -0.3458 0.07909 0.07611 -0.0325 0.9870 0.0346
-5.250 -0.3027 0.07361 0.07057 -0.0462 0.9830 0.0384
-5.000 -0.2402 0.06713 0.06389 -0.0672 0.9760 0.0401
-4.750 -0.2292 0.06106 0.05788 -0.0684 0.9730 0.0419
-4.500 -0.2034 0.05818 0.05495 -0.0708 0.9706 0.0449
-4.250 -0.1338 0.04974 0.04606 -0.0906 0.9663 0.0542
-4.000 -0.1169 0.04727 0.04370 -0.0902 0.9624 0.0567
-3.750 -0.0739 0.04350 0.03974 -0.0969 0.9601 0.0631
-3.500 -0.0214 0.03821 0.03412 -0.1063 0.9588 0.0706
-2.500 0.1759 0.02198 0.01554 -0.1275 0.9558 0.0468
-2.250 0.2117 0.02042 0.01340 -0.1285 0.9522 0.0411
-2.000 0.2477 0.01951 0.01229 -0.1300 0.9492 0.0400
-1.750 0.2863 0.01830 0.01096 -0.1321 0.9472 0.0400
-1.500 0.3266 0.01717 0.00978 -0.1347 0.9456 0.0419
-1.250 0.3617 0.01665 0.00924 -0.1363 0.9420 0.0484
-1.000 0.3949 0.01620 0.00882 -0.1375 0.9370 0.0699
-0.750 0.4359 0.01492 0.00878 -0.1410 0.9350 0.4409
-0.500 0.4676 0.01401 0.00885 -0.1413 0.9326 0.7802
-0.250 0.4898 0.01374 0.00869 -0.1398 0.9253 1.0000
0.000 0.5273 0.01371 0.00852 -0.1417 0.9212 1.0000
0.250 0.5690 0.01359 0.00828 -0.1443 0.9186 1.0000
0.500 0.5969 0.01363 0.00824 -0.1443 0.9108 1.0000
0.750 0.6374 0.01343 0.00798 -0.1467 0.9072 1.0000
1.000 0.6818 0.01311 0.00762 -0.1497 0.9050 1.0000
1.250 0.7103 0.01306 0.00756 -0.1496 0.8965 1.0000
1.500 0.7544 0.01264 0.00714 -0.1524 0.8932 1.0000
1.750 0.7887 0.01241 0.00692 -0.1534 0.8865 1.0000
2.000 0.8271 0.01203 0.00656 -0.1549 0.8804 1.0000
2.250 0.8614 0.01173 0.00633 -0.1557 0.8724 1.0000
2.500 0.8996 0.01132 0.00596 -0.1571 0.8650 1.0000
2.750 0.9295 0.01114 0.00583 -0.1570 0.8538 1.0000
3.000 0.9603 0.01094 0.00568 -0.1570 0.8416 1.0000
3.250 0.9905 0.01075 0.00558 -0.1568 0.8276 1.0000
3.500 1.0202 0.01060 0.00547 -0.1565 0.8114 1.0000
3.750 1.0472 0.01054 0.00546 -0.1558 0.7918 1.0000
4.000 1.0744 0.01050 0.00544 -0.1550 0.7687 1.0000
4.250 1.0994 0.01053 0.00554 -0.1539 0.7398 1.0000
4.500 1.1231 0.01065 0.00561 -0.1524 0.6998 1.0000
4.750 1.1443 0.01094 0.00573 -0.1504 0.6395 1.0000
5.000 1.1584 0.01176 0.00598 -0.1472 0.5335 1.0000
5.250 1.1653 0.01319 0.00662 -0.1431 0.4033 1.0000
5.500 1.1766 0.01451 0.00739 -0.1403 0.3036 1.0000
5.750 1.1898 0.01585 0.00827 -0.1380 0.2152 1.0000
6.000 1.2023 0.01745 0.00925 -0.1358 0.1204 1.0000
6.250 1.2096 0.02002 0.01110 -0.1324 0.0302 1.0000
6.500 1.2240 0.02172 0.01289 -0.1298 0.0233 1.0000
6.750 1.2410 0.02301 0.01434 -0.1277 0.0214 1.0000
7.000 1.2571 0.02454 0.01600 -0.1255 0.0201 1.0000
7.250 1.2742 0.02628 0.01786 -0.1235 0.0192 1.0000
7.500 1.2941 0.02833 0.02004 -0.1220 0.0188 1.0000
7.750 1.3182 0.03084 0.02277 -0.1210 0.0186 1.0000
8.000 1.3436 0.03368 0.02589 -0.1202 0.0185 1.0000
8.250 1.3629 0.03578 0.02817 -0.1190 0.0172 1.0000
8.500 1.3810 0.03922 0.03185 -0.1178 0.0160 1.0000
8.750 1.3975 0.04247 0.03553 -0.1158 0.0163 1.0000
9.000 1.4070 0.04777 0.04164 -0.1120 0.0180 1.0000
9.250 1.4035 0.05451 0.04910 -0.1074 0.0204 1.0000
9.500 1.3957 0.06021 0.05521 -0.1035 0.0219 1.0000
9.750 1.3063 0.05918 0.05479 -0.0889 0.0219 1.0000
10.000 1.2832 0.06405 0.05991 -0.0845 0.0223 1.0000
10.250 1.2567 0.07000 0.06607 -0.0811 0.0229 1.0000
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Polar data table (+)
Polar graphs
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