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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 500,000
Max Cl/Cd: 107.39 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e421-il-500000.txt
Download as CSV file: xf-e421-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.2320   0.09015   0.08604  -0.1303   0.6594   0.0236
  -9.250   0.2394   0.08812   0.08394  -0.1306   0.6496   0.0242
  -9.000   0.2472   0.08599   0.08180  -0.1312   0.6408   0.0244
  -8.750   0.2526   0.08357   0.07934  -0.1318   0.6326   0.0253
  -8.500   0.2426   0.07938   0.07516  -0.1345   0.6276   0.0261
  -8.250   0.2542   0.07757   0.07334  -0.1343   0.6196   0.0263
  -8.000   0.2644   0.07586   0.07157  -0.1341   0.6123   0.0265
  -7.750   0.2756   0.07427   0.06997  -0.1340   0.6059   0.0268
  -7.500   0.2838   0.07240   0.06810  -0.1342   0.5995   0.0273
  -7.250   0.1193   0.02393   0.01882  -0.1777   0.6113   0.0155
  -7.000   0.1433   0.02109   0.01554  -0.1803   0.6049   0.0158
  -6.750   0.1679   0.01952   0.01363  -0.1811   0.5981   0.0160
  -6.500   0.1921   0.01813   0.01191  -0.1815   0.5918   0.0164
  -6.250   0.2177   0.01721   0.01091  -0.1817   0.5862   0.0169
  -6.000   0.2437   0.01656   0.01013  -0.1816   0.5802   0.0174
  -5.750   0.2698   0.01602   0.00942  -0.1815   0.5745   0.0180
  -5.500   0.2965   0.01544   0.00870  -0.1814   0.5694   0.0186
  -5.250   0.3236   0.01496   0.00808  -0.1813   0.5641   0.0192
  -5.000   0.3499   0.01436   0.00740  -0.1812   0.5590   0.0201
  -4.750   0.3768   0.01406   0.00698  -0.1810   0.5540   0.0212
  -4.500   0.4045   0.01367   0.00651  -0.1809   0.5501   0.0226
  -4.250   0.4318   0.01334   0.00615  -0.1808   0.5458   0.0249
  -4.000   0.4592   0.01303   0.00577  -0.1807   0.5417   0.0280
  -3.750   0.4866   0.01280   0.00545  -0.1806   0.5376   0.0328
  -3.500   0.5145   0.01254   0.00515  -0.1805   0.5339   0.0402
  -3.250   0.5421   0.01234   0.00494  -0.1803   0.5303   0.0499
  -3.000   0.5696   0.01218   0.00480  -0.1802   0.5265   0.0597
  -2.750   0.5971   0.01211   0.00470  -0.1800   0.5230   0.0692
  -2.500   0.6247   0.01210   0.00463  -0.1799   0.5196   0.0788
  -2.250   0.6526   0.01212   0.00462  -0.1798   0.5164   0.0890
  -2.000   0.6802   0.01206   0.00459  -0.1796   0.5137   0.0995
  -1.750   0.7077   0.01203   0.00458  -0.1795   0.5108   0.1102
  -1.500   0.7352   0.01201   0.00454  -0.1792   0.5077   0.1201
  -1.250   0.7625   0.01207   0.00456  -0.1790   0.5047   0.1299
  -1.000   0.7900   0.01212   0.00458  -0.1789   0.5017   0.1405
  -0.750   0.8182   0.01222   0.00464  -0.1789   0.4988   0.1501
  -0.500   0.8454   0.01224   0.00469  -0.1786   0.4967   0.1596
  -0.250   0.8726   0.01224   0.00471  -0.1784   0.4943   0.1690
   0.000   0.8998   0.01231   0.00476  -0.1782   0.4917   0.1782
   0.250   0.9269   0.01233   0.00478  -0.1780   0.4891   0.1876
   0.500   0.9539   0.01241   0.00484  -0.1777   0.4865   0.1967
   0.750   0.9814   0.01250   0.00490  -0.1776   0.4840   0.2060
   1.000   1.0098   0.01270   0.00505  -0.1777   0.4812   0.2156
   1.250   1.0363   0.01271   0.00511  -0.1774   0.4796   0.2251
   1.500   1.0629   0.01276   0.00519  -0.1772   0.4775   0.2350
   1.750   1.0893   0.01280   0.00526  -0.1769   0.4751   0.2454
   2.000   1.1159   0.01288   0.00535  -0.1766   0.4727   0.2563
   2.250   1.1424   0.01293   0.00543  -0.1764   0.4705   0.2684
   2.500   1.1691   0.01303   0.00554  -0.1762   0.4684   0.2823
   2.750   1.1965   0.01318   0.00569  -0.1761   0.4662   0.2982
   3.000   1.2250   0.01340   0.00592  -0.1764   0.4637   0.3189
   3.250   1.2502   0.01342   0.00606  -0.1759   0.4621   0.3456
   3.500   1.2755   0.01344   0.00621  -0.1755   0.4600   0.3853
   3.750   1.3008   0.01331   0.00642  -0.1753   0.4579   0.5212
   4.000   1.3247   0.01276   0.00661  -0.1745   0.4558   1.0000
   4.250   1.3506   0.01292   0.00674  -0.1742   0.4538   1.0000
   4.500   1.3764   0.01310   0.00688  -0.1739   0.4519   1.0000
   4.750   1.4027   0.01331   0.00704  -0.1737   0.4497   1.0000
   5.000   1.4310   0.01365   0.00730  -0.1739   0.4471   1.0000
   5.250   1.4554   0.01382   0.00750  -0.1734   0.4454   1.0000
   5.500   1.4792   0.01397   0.00769  -0.1727   0.4436   1.0000
   5.750   1.5033   0.01415   0.00788  -0.1721   0.4416   1.0000
   6.000   1.5273   0.01432   0.00806  -0.1715   0.4394   1.0000
   6.250   1.5514   0.01449   0.00825  -0.1710   0.4372   1.0000
   6.500   1.5755   0.01468   0.00842  -0.1704   0.4351   1.0000
   6.750   1.6001   0.01490   0.00862  -0.1700   0.4330   1.0000
   7.000   1.6278   0.01525   0.00893  -0.1703   0.4303   1.0000
   7.250   1.6497   0.01546   0.00919  -0.1694   0.4284   1.0000
   7.500   1.6695   0.01562   0.00941  -0.1680   0.4261   1.0000
   7.750   1.6894   0.01579   0.00963  -0.1667   0.4236   1.0000
   8.000   1.7087   0.01595   0.00981  -0.1653   0.4210   1.0000
   8.250   1.7283   0.01613   0.01000  -0.1640   0.4185   1.0000
   8.500   1.7494   0.01636   0.01022  -0.1629   0.4158   1.0000
   8.750   1.7749   0.01672   0.01055  -0.1629   0.4128   1.0000
   9.000   1.7883   0.01691   0.01084  -0.1604   0.4107   1.0000
   9.250   1.8037   0.01713   0.01114  -0.1584   0.4079   1.0000
   9.500   1.8202   0.01736   0.01142  -0.1566   0.4051   1.0000
   9.750   1.8374   0.01761   0.01169  -0.1551   0.4024   1.0000
  10.000   1.8559   0.01789   0.01198  -0.1537   0.3996   1.0000
  10.250   1.8763   0.01826   0.01234  -0.1529   0.3965   1.0000
  10.500   1.8873   0.01859   0.01279  -0.1503   0.3937   1.0000
  10.750   1.9002   0.01895   0.01323  -0.1481   0.3904   1.0000
  11.000   1.9134   0.01932   0.01365  -0.1461   0.3870   1.0000
  11.250   1.9280   0.01973   0.01406  -0.1444   0.3837   1.0000
  11.500   1.9431   0.02022   0.01458  -0.1428   0.3803   1.0000
  11.750   1.9527   0.02078   0.01526  -0.1405   0.3770   1.0000
  12.000   1.9631   0.02137   0.01593  -0.1384   0.3732   1.0000
  12.250   1.9737   0.02201   0.01660  -0.1364   0.3694   1.0000
  12.500   1.9852   0.02272   0.01732  -0.1346   0.3654   1.0000
  12.750   1.9925   0.02359   0.01832  -0.1324   0.3613   1.0000
  13.000   1.9999   0.02452   0.01932  -0.1304   0.3567   1.0000
  13.250   2.0064   0.02557   0.02038  -0.1283   0.3521   1.0000
  13.500   2.0122   0.02676   0.02167  -0.1264   0.3472   1.0000
  13.750   2.0164   0.02810   0.02309  -0.1245   0.3415   1.0000
  14.000   2.0184   0.02967   0.02465  -0.1225   0.3363   1.0000
  14.250   2.0221   0.03127   0.02639  -0.1209   0.3304   1.0000
  14.500   2.0211   0.03327   0.02842  -0.1190   0.3240   1.0000
  14.750   2.0201   0.03541   0.03063  -0.1174   0.3174   1.0000
  15.000   2.0153   0.03798   0.03324  -0.1157   0.3099   1.0000
  15.250   2.0106   0.04068   0.03601  -0.1143   0.3025   1.0000
  15.500   2.0009   0.04394   0.03929  -0.1128   0.2944   1.0000
  15.750   1.9919   0.04732   0.04274  -0.1116   0.2859   1.0000
  16.000   1.9762   0.05149   0.04692  -0.1104   0.2772   1.0000
  16.250   1.9633   0.05556   0.05105  -0.1095   0.2679   1.0000
  16.500   1.9475   0.06006   0.05558  -0.1087   0.2589   1.0000
  16.750   1.9269   0.06527   0.06079  -0.1081   0.2493   1.0000
  17.000   1.9110   0.07007   0.06564  -0.1077   0.2398   1.0000
  17.250   1.8940   0.07511   0.07071  -0.1076   0.2310   1.0000
  17.500   1.8745   0.08059   0.07618  -0.1076   0.2222   1.0000
  17.750   1.8624   0.08524   0.08089  -0.1077   0.2138   1.0000
  18.000   1.8474   0.09030   0.08595  -0.1080   0.2057   1.0000
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