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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.81 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e422-il-1000000-n5.txt
Download as CSV file: xf-e422-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2200   0.05220   0.04841  -0.1047   0.5600   0.0059
  -9.500  -0.2567   0.04228   0.03839  -0.1143   0.5582   0.0058
  -9.250  -0.2789   0.02794   0.02360  -0.1280   0.5560   0.0057
  -9.000  -0.2642   0.02298   0.01826  -0.1312   0.5498   0.0057
  -8.750  -0.2445   0.02105   0.01610  -0.1316   0.5437   0.0058
  -8.500  -0.2230   0.01967   0.01452  -0.1316   0.5370   0.0058
  -8.250  -0.2010   0.01850   0.01314  -0.1313   0.5301   0.0058
  -8.000  -0.1774   0.01757   0.01207  -0.1311   0.5249   0.0058
  -7.750  -0.1534   0.01673   0.01107  -0.1307   0.5192   0.0058
  -7.500  -0.1290   0.01603   0.01023  -0.1303   0.5136   0.0058
  -7.250  -0.1040   0.01537   0.00944  -0.1299   0.5091   0.0059
  -7.000  -0.0786   0.01479   0.00873  -0.1296   0.5040   0.0059
  -6.750  -0.0530   0.01428   0.00810  -0.1292   0.4984   0.0059
  -6.500  -0.0271   0.01382   0.00754  -0.1288   0.4935   0.0059
  -6.250  -0.0013   0.01324   0.00685  -0.1284   0.4892   0.0060
  -6.000   0.0246   0.01271   0.00620  -0.1280   0.4847   0.0061
  -5.750   0.0510   0.01229   0.00568  -0.1276   0.4803   0.0063
  -5.500   0.0778   0.01197   0.00528  -0.1272   0.4765   0.0064
  -5.250   0.1051   0.01169   0.00495  -0.1269   0.4732   0.0066
  -5.000   0.1324   0.01145   0.00464  -0.1266   0.4692   0.0068
  -4.750   0.1597   0.01124   0.00437  -0.1263   0.4649   0.0070
  -4.250   0.2146   0.01087   0.00388  -0.1258   0.4577   0.0075
  -4.000   0.2423   0.01069   0.00367  -0.1255   0.4548   0.0079
  -3.750   0.2700   0.01055   0.00348  -0.1253   0.4516   0.0081
  -3.500   0.2975   0.01038   0.00326  -0.1250   0.4484   0.0087
  -3.250   0.3250   0.01027   0.00311  -0.1247   0.4448   0.0093
  -3.000   0.3527   0.01017   0.00297  -0.1244   0.4419   0.0101
  -2.750   0.3806   0.01005   0.00283  -0.1242   0.4393   0.0111
  -2.500   0.4084   0.00994   0.00271  -0.1240   0.4365   0.0129
  -2.250   0.4362   0.00985   0.00261  -0.1238   0.4337   0.0158
  -2.000   0.4638   0.00976   0.00251  -0.1235   0.4310   0.0206
  -1.750   0.4911   0.00966   0.00242  -0.1233   0.4282   0.0311
  -1.500   0.5184   0.00953   0.00235  -0.1230   0.4256   0.0481
  -1.250   0.5458   0.00936   0.00228  -0.1228   0.4236   0.0768
  -1.000   0.5734   0.00925   0.00225  -0.1226   0.4211   0.1021
  -0.750   0.6009   0.00921   0.00225  -0.1224   0.4186   0.1213
  -0.500   0.6285   0.00918   0.00226  -0.1222   0.4162   0.1372
  -0.250   0.6560   0.00918   0.00227  -0.1220   0.4139   0.1487
   0.000   0.6833   0.00921   0.00229  -0.1218   0.4113   0.1582
   0.250   0.7108   0.00923   0.00231  -0.1215   0.4090   0.1660
   0.500   0.7386   0.00924   0.00233  -0.1214   0.4072   0.1728
   0.750   0.7663   0.00925   0.00236  -0.1212   0.4051   0.1810
   1.000   0.7939   0.00929   0.00238  -0.1210   0.4029   0.1867
   1.250   0.8212   0.00931   0.00242  -0.1208   0.4008   0.1962
   1.500   0.8485   0.00935   0.00247  -0.1206   0.3986   0.2036
   1.750   0.8755   0.00940   0.00252  -0.1203   0.3963   0.2128
   2.000   0.9023   0.00947   0.00259  -0.1200   0.3937   0.2223
   2.250   0.9295   0.00950   0.00265  -0.1198   0.3919   0.2339
   2.500   0.9568   0.00953   0.00271  -0.1196   0.3902   0.2457
   2.750   0.9840   0.00956   0.00278  -0.1194   0.3883   0.2590
   3.000   1.0109   0.00960   0.00286  -0.1192   0.3863   0.2765
   3.250   1.0376   0.00964   0.00295  -0.1190   0.3842   0.2978
   3.500   1.0640   0.00970   0.00304  -0.1187   0.3819   0.3204
   3.750   1.0900   0.00975   0.00315  -0.1183   0.3794   0.3528
   4.000   1.1158   0.00981   0.00328  -0.1180   0.3769   0.3896
   4.250   1.1422   0.00980   0.00339  -0.1177   0.3755   0.4370
   4.500   1.1616   0.00920   0.00360  -0.1162   0.3740   0.7957
   4.750   1.2116   0.00908   0.00379  -0.1210   0.3715   1.0000
   5.000   1.2368   0.00920   0.00389  -0.1205   0.3691   1.0000
   5.250   1.2618   0.00932   0.00401  -0.1200   0.3667   1.0000
   5.500   1.2864   0.00946   0.00413  -0.1194   0.3643   1.0000
   5.750   1.3106   0.00962   0.00427  -0.1187   0.3617   1.0000
   6.000   1.3359   0.00973   0.00438  -0.1183   0.3598   1.0000
   6.250   1.3610   0.00984   0.00452  -0.1178   0.3575   1.0000
   6.500   1.3857   0.00997   0.00465  -0.1173   0.3544   1.0000
   6.750   1.4096   0.01013   0.00479  -0.1166   0.3507   1.0000
   7.000   1.4326   0.01032   0.00497  -0.1158   0.3468   1.0000
   7.250   1.4569   0.01046   0.00512  -0.1152   0.3443   1.0000
   7.500   1.4810   0.01060   0.00527  -0.1146   0.3413   1.0000
   7.750   1.5044   0.01076   0.00544  -0.1139   0.3379   1.0000
   8.000   1.5268   0.01095   0.00563  -0.1131   0.3344   1.0000
   8.250   1.5485   0.01117   0.00584  -0.1121   0.3307   1.0000
   8.500   1.5715   0.01132   0.00602  -0.1113   0.3272   1.0000
   8.750   1.5925   0.01151   0.00622  -0.1102   0.3229   1.0000
   9.000   1.6113   0.01175   0.00645  -0.1087   0.3185   1.0000
   9.250   1.6303   0.01197   0.00669  -0.1073   0.3150   1.0000
   9.500   1.6503   0.01218   0.00692  -0.1060   0.3108   1.0000
   9.750   1.6684   0.01245   0.00719  -0.1045   0.3057   1.0000
  10.000   1.6853   0.01276   0.00751  -0.1028   0.3009   1.0000
  10.250   1.7040   0.01303   0.00779  -0.1015   0.2956   1.0000
  10.500   1.7194   0.01341   0.00817  -0.0996   0.2890   1.0000
  10.750   1.7358   0.01377   0.00854  -0.0980   0.2829   1.0000
  11.000   1.7496   0.01424   0.00899  -0.0960   0.2751   1.0000
  11.250   1.7638   0.01470   0.00946  -0.0941   0.2684   1.0000
  11.500   1.7748   0.01531   0.01006  -0.0918   0.2598   1.0000
  11.750   1.7854   0.01596   0.01070  -0.0896   0.2505   1.0000
  12.000   1.7921   0.01681   0.01152  -0.0870   0.2402   1.0000
  12.250   1.7969   0.01782   0.01251  -0.0844   0.2303   1.0000
  12.500   1.8023   0.01886   0.01355  -0.0820   0.2205   1.0000
  12.750   1.8035   0.02024   0.01492  -0.0794   0.2101   1.0000
  13.000   1.8036   0.02182   0.01649  -0.0770   0.2012   1.0000
  13.250   1.8036   0.02354   0.01822  -0.0749   0.1923   1.0000
  13.500   1.8022   0.02551   0.02020  -0.0731   0.1842   1.0000
  14.000   1.7940   0.03033   0.02505  -0.0698   0.1684   1.0000
  14.250   1.7860   0.03328   0.02802  -0.0684   0.1614   1.0000
  14.500   1.7842   0.03577   0.03057  -0.0675   0.1568   1.0000
  14.750   1.7723   0.03930   0.03412  -0.0663   0.1499   1.0000
  15.000   1.7658   0.04242   0.03730  -0.0656   0.1449   1.0000
  15.250   1.7531   0.04628   0.04120  -0.0648   0.1390   1.0000
  15.500   1.7433   0.04994   0.04491  -0.0643   0.1345   1.0000
  15.750   1.7326   0.05380   0.04881  -0.0639   0.1291   1.0000
  16.000   1.7181   0.05816   0.05322  -0.0636   0.1240   1.0000
  16.250   1.7103   0.06189   0.05700  -0.0636   0.1200   1.0000
  16.500   1.6982   0.06619   0.06134  -0.0636   0.1152   1.0000
  16.750   1.6876   0.07038   0.06559  -0.0637   0.1109   1.0000
  17.000   1.6804   0.07422   0.06947  -0.0640   0.1067   1.0000
  17.250   1.6673   0.07893   0.07420  -0.0644   0.1018   1.0000
  17.500   1.6615   0.08273   0.07807  -0.0649   0.0986   1.0000
  17.750   1.6546   0.08673   0.08209  -0.0654   0.0942   1.0000
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