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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 500,000
Max Cl/Cd: 109.93 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e421-il-500000-n5.txt
Download as CSV file: xf-e421-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.1938   0.08800   0.08338  -0.1276   0.5913   0.0105
  -8.750   0.0218   0.05014   0.04555  -0.1402   0.5869   0.0098
  -8.500  -0.0062   0.03894   0.03413  -0.1541   0.5841   0.0098
  -8.250   0.0026   0.02860   0.02338  -0.1691   0.5794   0.0098
  -8.000   0.0252   0.02284   0.01722  -0.1759   0.5740   0.0099
  -7.750   0.0504   0.02057   0.01469  -0.1780   0.5686   0.0101
  -7.500   0.0758   0.01925   0.01316  -0.1789   0.5625   0.0103
  -7.250   0.1012   0.01828   0.01199  -0.1793   0.5564   0.0105
  -7.000   0.1272   0.01749   0.01102  -0.1795   0.5512   0.0107
  -6.750   0.1536   0.01671   0.01011  -0.1798   0.5460   0.0109
  -6.500   0.1798   0.01604   0.00931  -0.1799   0.5410   0.0113
  -6.250   0.2061   0.01554   0.00867  -0.1798   0.5364   0.0116
  -6.000   0.2332   0.01507   0.00810  -0.1799   0.5324   0.0119
  -5.750   0.2603   0.01467   0.00760  -0.1798   0.5282   0.0124
  -5.500   0.2873   0.01430   0.00711  -0.1797   0.5237   0.0129
  -5.250   0.3142   0.01400   0.00668  -0.1795   0.5194   0.0134
  -5.000   0.3414   0.01365   0.00625  -0.1794   0.5155   0.0141
  -4.750   0.3690   0.01338   0.00591  -0.1793   0.5117   0.0153
  -4.500   0.3964   0.01313   0.00559  -0.1792   0.5080   0.0166
  -4.250   0.4236   0.01292   0.00532  -0.1790   0.5044   0.0185
  -4.000   0.4507   0.01272   0.00504  -0.1788   0.5010   0.0210
  -3.750   0.4781   0.01254   0.00481  -0.1786   0.4981   0.0244
  -3.500   0.5059   0.01236   0.00461  -0.1785   0.4953   0.0288
  -3.250   0.5334   0.01221   0.00444  -0.1783   0.4922   0.0349
  -3.000   0.5607   0.01209   0.00430  -0.1781   0.4888   0.0418
  -2.750   0.5878   0.01201   0.00419  -0.1779   0.4856   0.0494
  -2.500   0.6147   0.01195   0.00410  -0.1776   0.4826   0.0572
  -2.250   0.6421   0.01188   0.00403  -0.1774   0.4802   0.0662
  -2.000   0.6697   0.01181   0.00398  -0.1773   0.4779   0.0761
  -1.750   0.6972   0.01176   0.00395  -0.1771   0.4754   0.0861
  -1.500   0.7245   0.01174   0.00392  -0.1769   0.4729   0.0949
  -1.250   0.7515   0.01174   0.00390  -0.1766   0.4702   0.1041
  -1.000   0.7782   0.01175   0.00390  -0.1763   0.4674   0.1136
  -0.750   0.8048   0.01179   0.00392  -0.1759   0.4649   0.1222
  -0.500   0.8318   0.01183   0.00393  -0.1757   0.4628   0.1305
  -0.250   0.8591   0.01183   0.00397  -0.1755   0.4609   0.1397
   0.000   0.8862   0.01186   0.00399  -0.1752   0.4588   0.1478
   0.250   0.9131   0.01190   0.00405  -0.1750   0.4566   0.1570
   0.500   0.9396   0.01195   0.00409  -0.1746   0.4542   0.1648
   0.750   0.9660   0.01201   0.00415  -0.1743   0.4519   0.1735
   1.000   0.9920   0.01210   0.00420  -0.1739   0.4495   0.1809
   1.250   1.0179   0.01219   0.00429  -0.1735   0.4475   0.1896
   1.500   1.0443   0.01227   0.00437  -0.1732   0.4457   0.1978
   1.750   1.0709   0.01232   0.00446  -0.1729   0.4440   0.2060
   2.000   1.0972   0.01239   0.00455  -0.1726   0.4420   0.2151
   2.250   1.1232   0.01246   0.00464  -0.1722   0.4398   0.2230
   2.500   1.1489   0.01254   0.00474  -0.1718   0.4376   0.2331
   2.750   1.1744   0.01264   0.00485  -0.1714   0.4356   0.2426
   3.000   1.1995   0.01275   0.00497  -0.1709   0.4337   0.2542
   3.250   1.2244   0.01286   0.00511  -0.1704   0.4319   0.2671
   3.500   1.2491   0.01301   0.00526  -0.1698   0.4299   0.2807
   3.750   1.2745   0.01309   0.00541  -0.1694   0.4282   0.2989
   4.000   1.2995   0.01316   0.00556  -0.1689   0.4264   0.3206
   4.250   1.3239   0.01324   0.00571  -0.1683   0.4244   0.3461
   4.500   1.3479   0.01332   0.00589  -0.1677   0.4225   0.3825
   4.750   1.3716   0.01335   0.00608  -0.1671   0.4206   0.4542
   5.250   1.4166   0.01296   0.00653  -0.1653   0.4167   1.0000
   5.500   1.4388   0.01317   0.00671  -0.1643   0.4147   1.0000
   5.750   1.4615   0.01339   0.00691  -0.1635   0.4127   1.0000
   6.000   1.4848   0.01355   0.00710  -0.1627   0.4111   1.0000
   6.250   1.5078   0.01373   0.00731  -0.1620   0.4093   1.0000
   6.500   1.5302   0.01392   0.00752  -0.1611   0.4072   1.0000
   6.750   1.5521   0.01412   0.00773  -0.1602   0.4049   1.0000
   7.000   1.5736   0.01434   0.00796  -0.1592   0.4027   1.0000
   7.250   1.5944   0.01458   0.00820  -0.1581   0.4005   1.0000
   7.500   1.6144   0.01485   0.00846  -0.1569   0.3982   1.0000
   7.750   1.6351   0.01511   0.00873  -0.1559   0.3959   1.0000
   8.000   1.6561   0.01532   0.00901  -0.1549   0.3933   1.0000
   8.250   1.6761   0.01557   0.00930  -0.1537   0.3903   1.0000
   8.500   1.6952   0.01585   0.00960  -0.1525   0.3873   1.0000
   8.750   1.7132   0.01617   0.00993  -0.1511   0.3843   1.0000
   9.000   1.7302   0.01655   0.01030  -0.1495   0.3815   1.0000
   9.250   1.7496   0.01684   0.01066  -0.1484   0.3786   1.0000
   9.500   1.7680   0.01717   0.01105  -0.1472   0.3754   1.0000
   9.750   1.7848   0.01756   0.01147  -0.1457   0.3720   1.0000
  10.000   1.8004   0.01801   0.01194  -0.1441   0.3688   1.0000
  10.250   1.8149   0.01852   0.01246  -0.1424   0.3656   1.0000
  10.500   1.8320   0.01894   0.01297  -0.1411   0.3620   1.0000
  10.750   1.8467   0.01947   0.01355  -0.1396   0.3579   1.0000
  11.000   1.8591   0.02012   0.01422  -0.1378   0.3537   1.0000
  11.250   1.8710   0.02082   0.01495  -0.1360   0.3497   1.0000
  11.500   1.8845   0.02148   0.01568  -0.1345   0.3450   1.0000
  11.750   1.8952   0.02232   0.01656  -0.1327   0.3403   1.0000
  12.000   1.9031   0.02334   0.01760  -0.1307   0.3357   1.0000
  12.250   1.9144   0.02423   0.01857  -0.1292   0.3305   1.0000
  12.500   1.9208   0.02545   0.01983  -0.1273   0.3247   1.0000
  12.750   1.9265   0.02679   0.02121  -0.1255   0.3191   1.0000
  13.000   1.9323   0.02819   0.02266  -0.1238   0.3127   1.0000
  13.250   1.9325   0.03007   0.02456  -0.1218   0.3065   1.0000
  13.500   1.9363   0.03179   0.02634  -0.1203   0.2993   1.0000
  13.750   1.9322   0.03423   0.02880  -0.1184   0.2921   1.0000
  14.000   1.9307   0.03656   0.03118  -0.1169   0.2834   1.0000
  14.250   1.9243   0.03944   0.03409  -0.1153   0.2758   1.0000
  14.500   1.9150   0.04274   0.03742  -0.1138   0.2664   1.0000
  14.750   1.9059   0.04615   0.04087  -0.1125   0.2580   1.0000
  15.000   1.8899   0.05041   0.04516  -0.1112   0.2490   1.0000
  15.250   1.8774   0.05446   0.04925  -0.1102   0.2396   1.0000
  15.500   1.8625   0.05890   0.05372  -0.1094   0.2312   1.0000
  15.750   1.8447   0.06383   0.05867  -0.1088   0.2225   1.0000
  16.000   1.8327   0.06820   0.06309  -0.1084   0.2143   1.0000
  16.250   1.8157   0.07328   0.06819  -0.1082   0.2066   1.0000
  16.500   1.8047   0.07772   0.07267  -0.1081   0.1988   1.0000
  16.750   1.7909   0.08262   0.07760  -0.1082   0.1917   1.0000
  17.000   1.7813   0.08701   0.08202  -0.1084   0.1842   1.0000
  17.250   1.7709   0.09158   0.08662  -0.1087   0.1779   1.0000
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