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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 200,000
Max Cl/Cd: 72.78 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e422-il-200000-n5.txt
Download as CSV file: xf-e422-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0099   0.10710   0.10228  -0.0829   0.7119   0.0297
 -10.250   0.0128   0.10425   0.09938  -0.0844   0.6986   0.0300
 -10.000   0.0171   0.10154   0.09661  -0.0855   0.6860   0.0301
  -9.000   0.0379   0.08829   0.08315  -0.0885   0.6459   0.0188
  -8.750   0.0453   0.08599   0.08080  -0.0890   0.6372   0.0184
  -8.500   0.0514   0.08342   0.07822  -0.0897   0.6288   0.0180
  -8.250   0.0545   0.08041   0.07518  -0.0905   0.6218   0.0175
  -8.000   0.0443   0.07433   0.06912  -0.0928   0.6176   0.0159
  -7.750   0.0472   0.07155   0.06634  -0.0936   0.6105   0.0158
  -7.500   0.0497   0.06895   0.06372  -0.0943   0.6042   0.0157
  -7.250   0.0474   0.06582   0.06061  -0.0950   0.5984   0.0156
  -7.000   0.0425   0.06260   0.05742  -0.0961   0.5927   0.0155
  -6.500  -0.0053   0.02850   0.02211  -0.1265   0.5914   0.0140
  -6.250   0.0138   0.02602   0.01916  -0.1270   0.5852   0.0141
  -6.000   0.0353   0.02425   0.01705  -0.1271   0.5787   0.0145
  -5.750   0.0578   0.02277   0.01524  -0.1268   0.5721   0.0149
  -5.250   0.1055   0.02059   0.01247  -0.1259   0.5604   0.0157
  -5.000   0.1301   0.01979   0.01149  -0.1254   0.5547   0.0163
  -4.750   0.1552   0.01925   0.01082  -0.1250   0.5497   0.0171
  -4.500   0.1810   0.01873   0.01013  -0.1246   0.5446   0.0185
  -4.250   0.2066   0.01817   0.00947  -0.1242   0.5391   0.0196
  -4.000   0.2323   0.01772   0.00890  -0.1238   0.5341   0.0208
  -3.750   0.2583   0.01730   0.00830  -0.1233   0.5297   0.0220
  -3.500   0.2847   0.01686   0.00780  -0.1230   0.5249   0.0236
  -3.250   0.3114   0.01650   0.00731  -0.1226   0.5204   0.0260
  -3.000   0.3380   0.01617   0.00688  -0.1222   0.5164   0.0300
  -2.750   0.3644   0.01583   0.00646  -0.1218   0.5128   0.0384
  -2.500   0.3911   0.01542   0.00611  -0.1215   0.5087   0.0563
  -2.250   0.4178   0.01514   0.00593  -0.1213   0.5044   0.0869
  -2.000   0.4447   0.01505   0.00586  -0.1210   0.5004   0.1135
  -1.750   0.4718   0.01507   0.00582  -0.1207   0.4969   0.1358
  -1.500   0.4990   0.01513   0.00582  -0.1204   0.4938   0.1528
  -1.250   0.5262   0.01514   0.00584  -0.1201   0.4903   0.1662
  -1.000   0.5532   0.01515   0.00583  -0.1198   0.4867   0.1778
  -0.750   0.5802   0.01517   0.00577  -0.1195   0.4832   0.1882
  -0.500   0.6069   0.01518   0.00574  -0.1191   0.4800   0.1981
  -0.250   0.6339   0.01524   0.00570  -0.1188   0.4772   0.2076
   0.000   0.6607   0.01524   0.00573  -0.1185   0.4741   0.2178
   0.250   0.6875   0.01526   0.00576  -0.1182   0.4710   0.2278
   0.500   0.7141   0.01530   0.00579  -0.1179   0.4680   0.2391
   0.750   0.7406   0.01534   0.00583  -0.1175   0.4651   0.2505
   1.000   0.7672   0.01540   0.00585  -0.1172   0.4623   0.2637
   1.250   0.7939   0.01549   0.00590  -0.1169   0.4598   0.2789
   1.500   0.8200   0.01553   0.00603  -0.1165   0.4569   0.2962
   1.750   0.8461   0.01559   0.00615  -0.1161   0.4541   0.3177
   2.000   0.8721   0.01564   0.00628  -0.1158   0.4514   0.3437
   2.250   0.8980   0.01568   0.00641  -0.1154   0.4487   0.3793
   2.500   0.9235   0.01569   0.00652  -0.1150   0.4462   0.4318
   2.750   0.9458   0.01517   0.00666  -0.1139   0.4439   0.7008
   3.250   1.0208   0.01531   0.00704  -0.1178   0.4383   1.0000
   3.500   1.0460   0.01552   0.00723  -0.1173   0.4358   1.0000
   3.750   1.0711   0.01573   0.00741  -0.1168   0.4332   1.0000
   4.000   1.0962   0.01594   0.00757  -0.1163   0.4307   1.0000
   4.250   1.1215   0.01617   0.00773  -0.1158   0.4284   1.0000
   4.500   1.1474   0.01643   0.00791  -0.1155   0.4262   1.0000
   4.750   1.1714   0.01668   0.00819  -0.1148   0.4239   1.0000
   5.000   1.1954   0.01693   0.00848  -0.1142   0.4213   1.0000
   5.250   1.2194   0.01718   0.00875  -0.1136   0.4187   1.0000
   5.500   1.2433   0.01743   0.00900  -0.1130   0.4161   1.0000
   5.750   1.2674   0.01767   0.00923  -0.1124   0.4136   1.0000
   6.000   1.2921   0.01793   0.00946  -0.1119   0.4115   1.0000
   6.250   1.3176   0.01822   0.00972  -0.1116   0.4096   1.0000
   6.500   1.3394   0.01853   0.01010  -0.1107   0.4070   1.0000
   6.750   1.3613   0.01883   0.01047  -0.1098   0.4041   1.0000
   7.000   1.3835   0.01912   0.01081  -0.1089   0.4013   1.0000
   7.250   1.4060   0.01940   0.01114  -0.1082   0.3988   1.0000
   7.500   1.4287   0.01968   0.01142  -0.1074   0.3964   1.0000
   7.750   1.4526   0.01996   0.01167  -0.1069   0.3940   1.0000
   8.000   1.4736   0.02030   0.01209  -0.1059   0.3914   1.0000
   8.250   1.4920   0.02066   0.01256  -0.1046   0.3882   1.0000
   8.500   1.5110   0.02099   0.01296  -0.1033   0.3849   1.0000
   8.750   1.5304   0.02128   0.01330  -0.1021   0.3817   1.0000
   9.000   1.5514   0.02155   0.01357  -0.1011   0.3788   1.0000
   9.250   1.5705   0.02190   0.01395  -0.0999   0.3759   1.0000
   9.500   1.5836   0.02233   0.01453  -0.0977   0.3722   1.0000
   9.750   1.5968   0.02271   0.01501  -0.0955   0.3687   1.0000
  10.000   1.6111   0.02307   0.01542  -0.0935   0.3654   1.0000
  10.250   1.6285   0.02338   0.01573  -0.0921   0.3623   1.0000
  10.500   1.6389   0.02392   0.01638  -0.0897   0.3588   1.0000
  10.750   1.6473   0.02452   0.01711  -0.0872   0.3546   1.0000
  11.000   1.6577   0.02507   0.01773  -0.0850   0.3506   1.0000
  11.250   1.6715   0.02553   0.01821  -0.0833   0.3472   1.0000
  11.500   1.6782   0.02635   0.01915  -0.0810   0.3430   1.0000
  11.750   1.6832   0.02728   0.02021  -0.0786   0.3384   1.0000
  12.000   1.6912   0.02811   0.02110  -0.0767   0.3341   1.0000
  12.250   1.6993   0.02901   0.02205  -0.0749   0.3300   1.0000
  12.500   1.6991   0.03051   0.02372  -0.0727   0.3247   1.0000
  12.750   1.7028   0.03183   0.02511  -0.0710   0.3196   1.0000
  13.000   1.7071   0.03321   0.02654  -0.0695   0.3149   1.0000
  13.250   1.7030   0.03538   0.02886  -0.0679   0.3088   1.0000
  13.500   1.7037   0.03721   0.03073  -0.0666   0.3032   1.0000
  13.750   1.6981   0.03978   0.03343  -0.0653   0.2969   1.0000
  14.000   1.6929   0.04242   0.03615  -0.0643   0.2904   1.0000
  14.250   1.6863   0.04533   0.03913  -0.0635   0.2838   1.0000
  14.500   1.6766   0.04870   0.04259  -0.0628   0.2765   1.0000
  14.750   1.6679   0.05209   0.04605  -0.0623   0.2694   1.0000
  15.000   1.6559   0.05598   0.05000  -0.0620   0.2614   1.0000
  15.250   1.6445   0.05999   0.05409  -0.0619   0.2537   1.0000
  15.500   1.6347   0.06383   0.05793  -0.0618   0.2453   1.0000
  15.750   1.6206   0.06844   0.06263  -0.0621   0.2369   1.0000
  16.000   1.6117   0.07239   0.06659  -0.0623   0.2286   1.0000
  16.250   1.6000   0.07686   0.07112  -0.0627   0.2202   1.0000
  16.500   1.5914   0.08097   0.07526  -0.0632   0.2123   1.0000
  16.750   1.5836   0.08501   0.07930  -0.0637   0.2044   1.0000
  17.000   1.5752   0.08926   0.08360  -0.0644   0.1967   1.0000
  17.250   1.5695   0.09307   0.08740  -0.0650   0.1894   1.0000
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