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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 500,000
Max Cl/Cd: 108.97 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e422-il-500000-n5.txt
Download as CSV file: xf-e422-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 422 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0052   0.10187   0.09761  -0.0857   0.6026   0.0159
 -10.250   0.0110   0.09882   0.09456  -0.0869   0.5959   0.0159
  -9.750   0.0161   0.09061   0.08629  -0.0886   0.5840   0.0104
  -9.500   0.0246   0.08850   0.08417  -0.0893   0.5773   0.0103
  -9.250   0.0315   0.08610   0.08175  -0.0901   0.5705   0.0102
  -9.000   0.0362   0.08332   0.07895  -0.0910   0.5645   0.0100
  -8.750   0.0407   0.08043   0.07606  -0.0920   0.5589   0.0099
  -8.500  -0.1235   0.05141   0.04716  -0.1033   0.5737   0.0080
  -8.250  -0.1695   0.03194   0.02720  -0.1235   0.5740   0.0078
  -8.000  -0.1552   0.02582   0.02059  -0.1285   0.5681   0.0078
  -7.750  -0.1369   0.02333   0.01776  -0.1294   0.5619   0.0078
  -7.500  -0.1162   0.02166   0.01580  -0.1295   0.5550   0.0079
  -7.000  -0.0714   0.01922   0.01288  -0.1289   0.5424   0.0080
  -6.750  -0.0477   0.01831   0.01177  -0.1286   0.5363   0.0081
  -6.250   0.0006   0.01666   0.00978  -0.1277   0.5260   0.0083
  -6.000   0.0255   0.01597   0.00897  -0.1273   0.5206   0.0084
  -5.750   0.0509   0.01545   0.00833  -0.1269   0.5151   0.0087
  -5.500   0.0768   0.01501   0.00778  -0.1265   0.5103   0.0089
  -5.250   0.1031   0.01458   0.00726  -0.1261   0.5053   0.0091
  -5.000   0.1294   0.01420   0.00677  -0.1257   0.5004   0.0094
  -4.750   0.1557   0.01386   0.00632  -0.1253   0.4961   0.0098
  -4.500   0.1825   0.01354   0.00590  -0.1249   0.4924   0.0102
  -4.250   0.2096   0.01325   0.00553  -0.1246   0.4884   0.0105
  -4.000   0.2363   0.01292   0.00514  -0.1242   0.4842   0.0111
  -3.750   0.2631   0.01271   0.00484  -0.1239   0.4800   0.0117
  -3.500   0.2901   0.01252   0.00457  -0.1235   0.4763   0.0124
  -3.250   0.3176   0.01232   0.00431  -0.1233   0.4728   0.0133
  -3.000   0.3450   0.01213   0.00408  -0.1230   0.4694   0.0148
  -2.750   0.3722   0.01196   0.00388  -0.1226   0.4660   0.0175
  -2.500   0.3992   0.01181   0.00369  -0.1223   0.4628   0.0225
  -2.250   0.4260   0.01164   0.00352  -0.1220   0.4597   0.0328
  -2.000   0.4534   0.01143   0.00337  -0.1217   0.4568   0.0509
  -1.750   0.4804   0.01124   0.00328  -0.1215   0.4536   0.0785
  -1.500   0.5075   0.01114   0.00324  -0.1212   0.4504   0.1026
  -1.250   0.5347   0.01110   0.00322  -0.1209   0.4475   0.1210
  -1.000   0.5617   0.01110   0.00322  -0.1206   0.4447   0.1382
  -0.750   0.5889   0.01111   0.00323  -0.1203   0.4423   0.1510
  -0.500   0.6165   0.01109   0.00323  -0.1201   0.4398   0.1620
  -0.250   0.6440   0.01111   0.00323  -0.1199   0.4371   0.1709
   0.000   0.6712   0.01111   0.00325  -0.1196   0.4342   0.1796
   0.250   0.6983   0.01116   0.00325  -0.1193   0.4315   0.1870
   0.500   0.7251   0.01119   0.00328  -0.1190   0.4291   0.1958
   0.750   0.7519   0.01126   0.00332  -0.1187   0.4267   0.2042
   1.000   0.7790   0.01128   0.00336  -0.1184   0.4247   0.2133
   1.250   0.8062   0.01131   0.00341  -0.1182   0.4224   0.2230
   1.500   0.8332   0.01134   0.00347  -0.1179   0.4199   0.2341
   1.750   0.8600   0.01138   0.00353  -0.1176   0.4174   0.2458
   2.000   0.8866   0.01144   0.00360  -0.1173   0.4149   0.2600
   2.250   0.9129   0.01150   0.00368  -0.1170   0.4127   0.2757
   2.500   0.9390   0.01158   0.00378  -0.1166   0.4106   0.2955
   2.750   0.9653   0.01163   0.00389  -0.1163   0.4086   0.3198
   3.000   0.9918   0.01165   0.00400  -0.1160   0.4065   0.3494
   3.250   1.0180   0.01167   0.00412  -0.1157   0.4042   0.3889
   3.500   1.0437   0.01166   0.00426  -0.1153   0.4018   0.4464
   4.000   1.1131   0.01100   0.00464  -0.1184   0.3973   1.0000
   4.250   1.1379   0.01116   0.00476  -0.1178   0.3951   1.0000
   4.500   1.1625   0.01134   0.00490  -0.1172   0.3929   1.0000
   4.750   1.1880   0.01146   0.00503  -0.1168   0.3909   1.0000
   5.000   1.2132   0.01160   0.00517  -0.1163   0.3888   1.0000
   5.250   1.2382   0.01174   0.00533  -0.1158   0.3866   1.0000
   5.500   1.2628   0.01190   0.00548  -0.1152   0.3844   1.0000
   5.750   1.2871   0.01206   0.00563  -0.1146   0.3820   1.0000
   6.000   1.3108   0.01225   0.00580  -0.1139   0.3796   1.0000
   6.250   1.3342   0.01246   0.00600  -0.1131   0.3774   1.0000
   6.500   1.3586   0.01261   0.00618  -0.1126   0.3754   1.0000
   6.750   1.3828   0.01276   0.00637  -0.1120   0.3730   1.0000
   7.000   1.4063   0.01293   0.00657  -0.1113   0.3702   1.0000
   7.250   1.4293   0.01312   0.00676  -0.1105   0.3674   1.0000
   7.500   1.4512   0.01332   0.00696  -0.1095   0.3643   1.0000
   7.750   1.4723   0.01356   0.00719  -0.1085   0.3611   1.0000
   8.000   1.4952   0.01373   0.00741  -0.1077   0.3582   1.0000
   8.250   1.5168   0.01392   0.00764  -0.1067   0.3550   1.0000
   8.500   1.5367   0.01413   0.00788  -0.1054   0.3518   1.0000
   8.750   1.5548   0.01438   0.00813  -0.1039   0.3486   1.0000
   9.000   1.5728   0.01465   0.00842  -0.1023   0.3456   1.0000
   9.250   1.5927   0.01486   0.00870  -0.1011   0.3422   1.0000
   9.500   1.6111   0.01512   0.00900  -0.0996   0.3382   1.0000
   9.750   1.6280   0.01543   0.00933  -0.0980   0.3343   1.0000
  10.000   1.6439   0.01579   0.00969  -0.0962   0.3305   1.0000
  10.250   1.6625   0.01608   0.01006  -0.0950   0.3267   1.0000
  10.500   1.6787   0.01644   0.01046  -0.0934   0.3222   1.0000
  10.750   1.6927   0.01690   0.01093  -0.0915   0.3178   1.0000
  11.000   1.7081   0.01733   0.01142  -0.0899   0.3136   1.0000
  11.250   1.7229   0.01780   0.01194  -0.0883   0.3083   1.0000
  11.500   1.7333   0.01845   0.01260  -0.0862   0.3027   1.0000
  12.000   1.7566   0.01981   0.01405  -0.0826   0.2910   1.0000
  12.250   1.7646   0.02073   0.01499  -0.0806   0.2848   1.0000
  12.500   1.7726   0.02171   0.01603  -0.0788   0.2774   1.0000
  12.750   1.7772   0.02298   0.01731  -0.0768   0.2704   1.0000
  13.000   1.7809   0.02440   0.01877  -0.0750   0.2619   1.0000
  13.250   1.7823   0.02609   0.02049  -0.0732   0.2538   1.0000
  13.500   1.7790   0.02826   0.02267  -0.0714   0.2448   1.0000
  13.750   1.7781   0.03038   0.02483  -0.0700   0.2361   1.0000
  14.000   1.7707   0.03317   0.02764  -0.0685   0.2273   1.0000
  14.250   1.7617   0.03625   0.03075  -0.0672   0.2183   1.0000
  14.500   1.7531   0.03942   0.03396  -0.0661   0.2104   1.0000
  14.750   1.7380   0.04337   0.03793  -0.0652   0.2023   1.0000
  15.000   1.7294   0.04677   0.04138  -0.0645   0.1952   1.0000
  15.250   1.7125   0.05120   0.04585  -0.0639   0.1877   1.0000
  15.500   1.7010   0.05517   0.04987  -0.0636   0.1804   1.0000
  15.750   1.6864   0.05962   0.05435  -0.0634   0.1745   1.0000
  16.000   1.6757   0.06371   0.05849  -0.0634   0.1675   1.0000
  16.250   1.6610   0.06838   0.06319  -0.0636   0.1617   1.0000
  16.500   1.6526   0.07237   0.06723  -0.0638   0.1552   1.0000
  16.750   1.6396   0.07703   0.07191  -0.0642   0.1495   1.0000
  17.000   1.6332   0.08089   0.07583  -0.0646   0.1440   1.0000
  17.250   1.6223   0.08544   0.08041  -0.0652   0.1381   1.0000
  17.500   1.6160   0.08940   0.08443  -0.0658   0.1329   1.0000
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