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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 100,000
Max Cl/Cd: 48.01 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e421-il-100000-n5.txt
Download as CSV file: xf-e421-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 421 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1863   0.10092   0.09487  -0.1160   0.7502   0.0542
  -9.250   0.1896   0.09896   0.09286  -0.1184   0.7375   0.0561
  -9.000   0.2000   0.09648   0.09029  -0.1201   0.7262   0.0561
  -8.750   0.2039   0.09434   0.08813  -0.1217   0.7152   0.0563
  -8.500   0.2119   0.09181   0.08553  -0.1231   0.7062   0.0563
  -8.000   0.2336   0.08417   0.07775  -0.1240   0.6889   0.0381
  -7.500   0.2362   0.07804   0.07160  -0.1262   0.6737   0.0342
  -7.250   0.2444   0.07586   0.06936  -0.1266   0.6669   0.0339
  -7.000   0.2492   0.07363   0.06716  -0.1267   0.6593   0.0336
  -6.750   0.2525   0.07133   0.06485  -0.1269   0.6528   0.0333
  -6.500   0.2536   0.06909   0.06257  -0.1270   0.6472   0.0331
  -6.250   0.2561   0.06668   0.06020  -0.1277   0.6408   0.0329
  -6.000   0.2601   0.06378   0.05730  -0.1293   0.6354   0.0329
  -5.750   0.2668   0.06058   0.05405  -0.1319   0.6309   0.0330
  -5.500   0.2719   0.05558   0.04903  -0.1371   0.6263   0.0339
  -5.250   0.2854   0.05242   0.04586  -0.1406   0.6208   0.0349
  -5.000   0.3029   0.04871   0.04207  -0.1451   0.6157   0.0362
  -4.750   0.3412   0.02779   0.01942  -0.1720   0.6135   0.0390
  -4.500   0.3681   0.02700   0.01848  -0.1726   0.6086   0.0415
  -4.250   0.3946   0.02579   0.01699  -0.1733   0.6028   0.0456
  -4.000   0.4221   0.02472   0.01561  -0.1738   0.5977   0.0505
  -3.750   0.4504   0.02404   0.01468  -0.1742   0.5935   0.0568
  -3.500   0.4781   0.02358   0.01404  -0.1745   0.5893   0.0642
  -3.250   0.5045   0.02326   0.01363  -0.1744   0.5845   0.0727
  -3.000   0.5316   0.02300   0.01326  -0.1744   0.5799   0.0822
  -2.750   0.5594   0.02280   0.01290  -0.1744   0.5759   0.0926
  -2.500   0.5882   0.02266   0.01255  -0.1746   0.5725   0.1036
  -2.250   0.6132   0.02266   0.01257  -0.1741   0.5678   0.1135
  -2.000   0.6394   0.02264   0.01252  -0.1738   0.5636   0.1234
  -1.750   0.6666   0.02257   0.01231  -0.1737   0.5600   0.1342
  -1.500   0.6947   0.02252   0.01206  -0.1736   0.5569   0.1462
  -1.250   0.7230   0.02258   0.01207  -0.1737   0.5541   0.1563
  -1.000   0.7474   0.02263   0.01209  -0.1731   0.5501   0.1670
  -0.750   0.7727   0.02271   0.01211  -0.1726   0.5462   0.1783
  -0.500   0.7987   0.02276   0.01213  -0.1723   0.5426   0.1884
  -0.250   0.8260   0.02281   0.01203  -0.1721   0.5396   0.2005
   0.000   0.8538   0.02288   0.01205  -0.1721   0.5371   0.2113
   0.250   0.8805   0.02299   0.01208  -0.1719   0.5345   0.2226
   0.500   0.9034   0.02319   0.01232  -0.1711   0.5309   0.2338
   0.750   0.9274   0.02334   0.01249  -0.1705   0.5274   0.2444
   1.000   0.9528   0.02350   0.01258  -0.1700   0.5243   0.2573
   1.250   0.9789   0.02360   0.01268  -0.1697   0.5215   0.2691
   1.500   1.0066   0.02373   0.01275  -0.1697   0.5192   0.2827
   1.750   1.0348   0.02391   0.01284  -0.1698   0.5171   0.2977
   2.000   1.0552   0.02426   0.01330  -0.1686   0.5138   0.3123
   2.250   1.0770   0.02456   0.01368  -0.1677   0.5105   0.3285
   2.500   1.1004   0.02481   0.01398  -0.1670   0.5075   0.3480
   2.750   1.1254   0.02502   0.01422  -0.1666   0.5048   0.3726
   3.000   1.1518   0.02517   0.01443  -0.1665   0.5025   0.4079
   3.250   1.1791   0.02519   0.01465  -0.1666   0.5005   0.4835
   3.750   1.2168   0.02549   0.01563  -0.1636   0.4949   1.0000
   4.000   1.2356   0.02607   0.01620  -0.1623   0.4917   1.0000
   4.250   1.2568   0.02657   0.01666  -0.1613   0.4888   1.0000
   4.500   1.2800   0.02702   0.01705  -0.1607   0.4865   1.0000
   4.750   1.3053   0.02742   0.01738  -0.1604   0.4844   1.0000
   5.000   1.3331   0.02777   0.01763  -0.1605   0.4825   1.0000
   5.250   1.3521   0.02840   0.01827  -0.1594   0.4800   1.0000
   5.500   1.3598   0.02937   0.01936  -0.1565   0.4763   1.0000
   5.750   1.3731   0.03017   0.02022  -0.1545   0.4732   1.0000
   6.000   1.3901   0.03085   0.02093  -0.1531   0.4706   1.0000
   6.250   1.4110   0.03137   0.02144  -0.1522   0.4683   1.0000
   6.500   1.4367   0.03173   0.02176  -0.1521   0.4662   1.0000
   6.750   1.4670   0.03198   0.02195  -0.1526   0.4644   1.0000
   7.000   1.4588   0.03352   0.02368  -0.1477   0.4606   1.0000
   7.250   1.4460   0.03522   0.02554  -0.1422   0.4567   1.0000
   7.500   1.4499   0.03640   0.02678  -0.1393   0.4534   1.0000
   7.750   1.4668   0.03704   0.02744  -0.1380   0.4509   1.0000
   8.000   1.4923   0.03734   0.02773  -0.1378   0.4489   1.0000
   8.250   1.5264   0.03735   0.02770  -0.1387   0.4473   1.0000
   8.500   1.3867   0.04722   0.03806  -0.1233   0.4353   1.0000
   8.750   1.4097   0.04753   0.03838  -0.1228   0.4332   1.0000
   9.000   1.4415   0.04716   0.03800  -0.1228   0.4318   1.0000
   9.250   1.4778   0.04653   0.03734  -0.1233   0.4306   1.0000
   9.750   1.3778   0.06035   0.05147  -0.1162   0.4131   1.0000
  10.750   1.2042   0.09534   0.08693  -0.1153   0.3620   1.0000
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