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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.92 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e422-il-1000000.txt
Download as CSV file: xf-e422-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0574   0.08731   0.08382  -0.0936   0.5883   0.0141
  -9.000   0.0641   0.08486   0.08135  -0.0944   0.5813   0.0145
  -8.750   0.0698   0.08216   0.07864  -0.0953   0.5746   0.0148
  -8.500   0.0745   0.07945   0.07591  -0.0962   0.5679   0.0151
  -8.250   0.0653   0.07351   0.07000  -0.0988   0.5645   0.0159
  -8.000   0.0678   0.07039   0.06689  -0.0999   0.5590   0.0159
  -7.750   0.0626   0.06659   0.06311  -0.1008   0.5541   0.0161
  -7.500   0.0646   0.06424   0.06074  -0.1012   0.5479   0.0162
  -7.250  -0.0641   0.02405   0.01955  -0.1322   0.5609   0.0106
  -7.000  -0.0494   0.02114   0.01641  -0.1321   0.5544   0.0101
  -6.750  -0.0311   0.01897   0.01390  -0.1317   0.5476   0.0099
  -6.500  -0.0098   0.01729   0.01195  -0.1312   0.5419   0.0097
  -6.250   0.0131   0.01609   0.01051  -0.1306   0.5356   0.0096
  -6.000   0.0368   0.01512   0.00933  -0.1299   0.5295   0.0095
  -5.750   0.0618   0.01428   0.00834  -0.1294   0.5246   0.0095
  -5.500   0.0871   0.01362   0.00754  -0.1289   0.5192   0.0095
  -5.250   0.1125   0.01309   0.00687  -0.1283   0.5133   0.0095
  -5.000   0.1389   0.01258   0.00627  -0.1279   0.5089   0.0096
  -4.750   0.1654   0.01214   0.00574  -0.1275   0.5040   0.0097
  -4.500   0.1918   0.01178   0.00527  -0.1270   0.4989   0.0099
  -4.250   0.2185   0.01148   0.00488  -0.1266   0.4941   0.0101
  -4.000   0.2460   0.01120   0.00454  -0.1263   0.4907   0.0104
  -3.750   0.2728   0.01077   0.00403  -0.1259   0.4867   0.0110
  -3.500   0.3000   0.01055   0.00375  -0.1256   0.4827   0.0117
  -3.250   0.3270   0.01042   0.00355  -0.1252   0.4778   0.0126
  -3.000   0.3548   0.01019   0.00328  -0.1249   0.4749   0.0137
  -2.750   0.3826   0.01001   0.00307  -0.1247   0.4716   0.0153
  -2.500   0.4102   0.00983   0.00287  -0.1244   0.4682   0.0186
  -2.250   0.4373   0.00961   0.00266  -0.1241   0.4648   0.0314
  -2.000   0.4638   0.00941   0.00254  -0.1237   0.4609   0.0601
  -1.750   0.4913   0.00925   0.00247  -0.1235   0.4584   0.0876
  -1.500   0.5192   0.00915   0.00244  -0.1233   0.4559   0.1078
  -1.250   0.5469   0.00909   0.00243  -0.1231   0.4529   0.1263
  -1.000   0.5745   0.00907   0.00243  -0.1229   0.4498   0.1418
  -0.750   0.6019   0.00910   0.00245  -0.1227   0.4467   0.1543
  -0.500   0.6288   0.00916   0.00251  -0.1224   0.4432   0.1669
  -0.250   0.6568   0.00914   0.00251  -0.1222   0.4414   0.1769
   0.000   0.6848   0.00915   0.00253  -0.1221   0.4393   0.1856
   0.250   0.7126   0.00914   0.00253  -0.1219   0.4368   0.1949
   0.500   0.7402   0.00916   0.00255  -0.1217   0.4342   0.2031
   0.750   0.7674   0.00919   0.00257  -0.1214   0.4316   0.2126
   1.000   0.7943   0.00926   0.00262  -0.1211   0.4286   0.2217
   1.250   0.8211   0.00933   0.00270  -0.1208   0.4258   0.2331
   1.500   0.8489   0.00933   0.00273  -0.1207   0.4243   0.2446
   1.750   0.8764   0.00934   0.00278  -0.1205   0.4223   0.2596
   2.000   0.9038   0.00934   0.00283  -0.1204   0.4201   0.2780
   2.250   0.9308   0.00935   0.00289  -0.1201   0.4177   0.3017
   2.500   0.9575   0.00938   0.00297  -0.1199   0.4154   0.3328
   2.750   0.9837   0.00942   0.00308  -0.1195   0.4129   0.3706
   3.000   1.0093   0.00948   0.00323  -0.1191   0.4099   0.4250
   3.250   1.0279   0.00876   0.00342  -0.1174   0.4084   0.8005
   3.500   1.0856   0.00862   0.00357  -0.1238   0.4063   1.0000
   3.750   1.1115   0.00871   0.00364  -0.1233   0.4042   1.0000
   4.000   1.1372   0.00880   0.00372  -0.1228   0.4021   1.0000
   4.250   1.1626   0.00892   0.00381  -0.1223   0.4000   1.0000
   4.500   1.1877   0.00905   0.00392  -0.1218   0.3977   1.0000
   4.750   1.2121   0.00922   0.00405  -0.1211   0.3949   1.0000
   5.000   1.2371   0.00938   0.00419  -0.1206   0.3925   1.0000
   5.250   1.2629   0.00946   0.00429  -0.1202   0.3909   1.0000
   5.500   1.2885   0.00955   0.00440  -0.1197   0.3890   1.0000
   5.750   1.3139   0.00965   0.00450  -0.1193   0.3868   1.0000
   6.000   1.3389   0.00977   0.00462  -0.1188   0.3844   1.0000
   6.250   1.3634   0.00991   0.00475  -0.1182   0.3819   1.0000
   6.500   1.3867   0.01012   0.00492  -0.1174   0.3785   1.0000
   6.750   1.4113   0.01025   0.00507  -0.1169   0.3759   1.0000
   7.000   1.4365   0.01034   0.00519  -0.1165   0.3736   1.0000
   7.250   1.4612   0.01044   0.00532  -0.1160   0.3711   1.0000
   7.500   1.4852   0.01058   0.00546  -0.1154   0.3683   1.0000
   7.750   1.5083   0.01075   0.00562  -0.1146   0.3654   1.0000
   8.000   1.5300   0.01100   0.00585  -0.1136   0.3619   1.0000
   8.250   1.5541   0.01110   0.00600  -0.1131   0.3596   1.0000
   8.500   1.5781   0.01121   0.00615  -0.1125   0.3568   1.0000
   8.750   1.6009   0.01136   0.00631  -0.1117   0.3536   1.0000
   9.000   1.6216   0.01155   0.00651  -0.1106   0.3503   1.0000
   9.250   1.6396   0.01181   0.00676  -0.1089   0.3467   1.0000
   9.500   1.6611   0.01195   0.00694  -0.1079   0.3440   1.0000
   9.750   1.6822   0.01210   0.00714  -0.1068   0.3408   1.0000
  10.000   1.7016   0.01230   0.00736  -0.1055   0.3371   1.0000
  10.250   1.7185   0.01259   0.00764  -0.1038   0.3330   1.0000
  10.500   1.7377   0.01282   0.00791  -0.1025   0.3293   1.0000
  10.750   1.7577   0.01303   0.00816  -0.1014   0.3252   1.0000
  11.000   1.7750   0.01333   0.00847  -0.0999   0.3207   1.0000
  11.250   1.7899   0.01372   0.00886  -0.0980   0.3160   1.0000
  11.500   1.8093   0.01396   0.00916  -0.0969   0.3116   1.0000
  11.750   1.8249   0.01435   0.00956  -0.0952   0.3058   1.0000
  12.000   1.8382   0.01483   0.01005  -0.0933   0.3005   1.0000
  12.250   1.8544   0.01522   0.01048  -0.0919   0.2945   1.0000
  12.500   1.8639   0.01590   0.01115  -0.0895   0.2874   1.0000
  12.750   1.8779   0.01641   0.01170  -0.0879   0.2808   1.0000
  13.000   1.8843   0.01731   0.01258  -0.0855   0.2728   1.0000
  13.250   1.8942   0.01809   0.01339  -0.0836   0.2643   1.0000
  13.500   1.8983   0.01924   0.01454  -0.0812   0.2553   1.0000
  13.750   1.9005   0.02059   0.01589  -0.0789   0.2459   1.0000
  14.000   1.9021   0.02211   0.01741  -0.0767   0.2360   1.0000
  14.250   1.8991   0.02406   0.01936  -0.0745   0.2260   1.0000
  14.500   1.8919   0.02649   0.02178  -0.0723   0.2157   1.0000
  14.750   1.8869   0.02893   0.02424  -0.0707   0.2065   1.0000
  15.000   1.8781   0.03182   0.02714  -0.0691   0.1977   1.0000
  15.250   1.8648   0.03527   0.03061  -0.0676   0.1895   1.0000
  15.500   1.8566   0.03839   0.03377  -0.0665   0.1824   1.0000
  15.750   1.8401   0.04242   0.03783  -0.0654   0.1756   1.0000
  16.000   1.8293   0.04602   0.04148  -0.0647   0.1689   1.0000
  16.250   1.8108   0.05058   0.04607  -0.0640   0.1628   1.0000
  16.500   1.8008   0.05432   0.04987  -0.0636   0.1572   1.0000
  16.750   1.7827   0.05905   0.05463  -0.0634   0.1510   1.0000
  17.000   1.7707   0.06324   0.05887  -0.0633   0.1456   1.0000
  17.250   1.7570   0.06770   0.06338  -0.0634   0.1403   1.0000
  17.500   1.7421   0.07242   0.06813  -0.0636   0.1351   1.0000
  17.750   1.7332   0.07649   0.07225  -0.0639   0.1302   1.0000
  18.000   1.7173   0.08151   0.07728  -0.0645   0.1246   1.0000
  18.250   1.7106   0.08543   0.08127  -0.0650   0.1203   1.0000
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