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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 200,000
Max Cl/Cd: 60.01 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e422-il-200000.txt
Download as CSV file: xf-e422-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0711   0.09984   0.09597  -0.0808   0.7861   0.0440
 -10.250   0.0657   0.09750   0.09354  -0.0830   0.7706   0.0451
 -10.000   0.0636   0.09479   0.09076  -0.0843   0.7552   0.0454
  -9.750   0.0837   0.09149   0.08734  -0.0829   0.7371   0.0462
  -9.500   0.0923   0.08901   0.08478  -0.0831   0.7234   0.0469
  -9.250   0.0993   0.08651   0.08219  -0.0834   0.7122   0.0480
  -9.000   0.1043   0.08386   0.07950  -0.0841   0.7012   0.0496
  -8.750   0.0937   0.08140   0.07700  -0.0869   0.6947   0.0512
  -8.500   0.0808   0.08799   0.08347  -0.0926   0.7188   0.0500
  -8.250   0.0603   0.08587   0.08137  -0.0976   0.7092   0.0515
  -8.000   0.0785   0.08302   0.07842  -0.0959   0.6970   0.0519
  -7.750   0.0948   0.08079   0.07613  -0.0948   0.6849   0.0529
  -7.500   0.1037   0.07874   0.07400  -0.0949   0.6756   0.0541
  -7.250   0.1089   0.07655   0.07182  -0.0954   0.6658   0.0560
  -7.000   0.0857   0.07427   0.06956  -0.0998   0.6600   0.0583
  -6.750   0.0949   0.07137   0.06666  -0.0994   0.6518   0.0589
  -6.500   0.1107   0.06947   0.06470  -0.0976   0.6437   0.0600
  -6.250   0.1207   0.06750   0.06268  -0.0980   0.6370   0.0611
  -6.000   0.1285   0.06517   0.06036  -0.0996   0.6300   0.0635
  -5.750   0.1310   0.06034   0.05550  -0.1081   0.6252   0.0669
  -5.500   0.1167   0.03423   0.02862  -0.1285   0.6267   0.0343
  -5.250   0.1340   0.03056   0.02455  -0.1297   0.6214   0.0329
  -5.000   0.1492   0.02467   0.01730  -0.1304   0.6160   0.0304
  -4.750   0.1723   0.02300   0.01530  -0.1299   0.6094   0.0305
  -4.500   0.1970   0.02179   0.01384  -0.1294   0.6038   0.0312
  -4.250   0.2220   0.02089   0.01281  -0.1289   0.5975   0.0324
  -4.000   0.2482   0.02021   0.01175  -0.1283   0.5915   0.0347
  -3.750   0.2738   0.01938   0.01090  -0.1280   0.5866   0.0369
  -3.500   0.3002   0.01872   0.01007  -0.1274   0.5817   0.0389
  -3.250   0.3257   0.01799   0.00934  -0.1268   0.5762   0.0414
  -3.000   0.3521   0.01743   0.00869  -0.1262   0.5713   0.0458
  -2.750   0.3790   0.01698   0.00819  -0.1259   0.5670   0.0557
  -2.500   0.4051   0.01640   0.00774  -0.1254   0.5622   0.0859
  -2.250   0.4323   0.01640   0.00786  -0.1251   0.5574   0.1328
  -2.000   0.4599   0.01663   0.00802  -0.1249   0.5532   0.1565
  -1.750   0.4878   0.01692   0.00822  -0.1248   0.5495   0.1757
  -1.500   0.5146   0.01709   0.00835  -0.1244   0.5454   0.1917
  -1.250   0.5411   0.01718   0.00838  -0.1240   0.5409   0.2059
  -1.000   0.5681   0.01716   0.00837  -0.1237   0.5368   0.2192
  -0.750   0.5956   0.01712   0.00826  -0.1235   0.5334   0.2312
  -0.500   0.6241   0.01725   0.00823  -0.1235   0.5303   0.2438
  -0.250   0.6497   0.01722   0.00831  -0.1230   0.5267   0.2556
   0.000   0.6759   0.01720   0.00831  -0.1226   0.5228   0.2677
   0.250   0.7029   0.01721   0.00829  -0.1223   0.5192   0.2813
   0.500   0.7303   0.01722   0.00828  -0.1221   0.5160   0.2961
   0.750   0.7584   0.01731   0.00833  -0.1221   0.5131   0.3124
   1.000   0.7839   0.01740   0.00851  -0.1216   0.5100   0.3306
   1.250   0.8091   0.01747   0.00869  -0.1211   0.5067   0.3532
   1.500   0.8346   0.01747   0.00883  -0.1207   0.5033   0.3814
   1.750   0.8606   0.01742   0.00892  -0.1203   0.5002   0.4280
   2.000   0.8825   0.01665   0.00900  -0.1191   0.4975   0.7118
   2.250   0.9392   0.01678   0.00917  -0.1248   0.4944   1.0000
   2.500   0.9625   0.01707   0.00948  -0.1240   0.4913   1.0000
   2.750   0.9868   0.01739   0.00977  -0.1234   0.4882   1.0000
   3.000   1.0119   0.01767   0.01001  -0.1228   0.4851   1.0000
   3.250   1.0381   0.01792   0.01018  -0.1225   0.4822   1.0000
   3.500   1.0655   0.01819   0.01034  -0.1224   0.4797   1.0000
   3.750   1.0934   0.01864   0.01066  -0.1224   0.4772   1.0000
   4.000   1.1150   0.01901   0.01112  -0.1214   0.4744   1.0000
   4.250   1.1375   0.01939   0.01156  -0.1206   0.4713   1.0000
   4.500   1.1614   0.01973   0.01191  -0.1199   0.4682   1.0000
   4.750   1.1867   0.02000   0.01215  -0.1195   0.4654   1.0000
   5.000   1.2136   0.02029   0.01237  -0.1194   0.4630   1.0000
   5.250   1.2415   0.02069   0.01270  -0.1195   0.4608   1.0000
   5.500   1.2630   0.02122   0.01330  -0.1186   0.4581   1.0000
   5.750   1.2829   0.02169   0.01387  -0.1174   0.4548   1.0000
   6.000   1.3050   0.02208   0.01431  -0.1165   0.4516   1.0000
   6.250   1.3291   0.02242   0.01467  -0.1160   0.4488   1.0000
   6.500   1.3549   0.02273   0.01496  -0.1158   0.4464   1.0000
   6.750   1.3833   0.02305   0.01521  -0.1160   0.4441   1.0000
   7.000   1.4044   0.02363   0.01587  -0.1151   0.4413   1.0000
   7.250   1.4208   0.02422   0.01660  -0.1135   0.4378   1.0000
   7.500   1.4408   0.02467   0.01712  -0.1124   0.4344   1.0000
   7.750   1.4647   0.02494   0.01741  -0.1118   0.4314   1.0000
   8.000   1.4916   0.02515   0.01760  -0.1118   0.4288   1.0000
   8.250   1.5228   0.02544   0.01780  -0.1125   0.4263   1.0000
   8.500   1.5325   0.02616   0.01873  -0.1099   0.4225   1.0000
   8.750   1.5479   0.02668   0.01939  -0.1081   0.4186   1.0000
   9.000   1.5700   0.02693   0.01968  -0.1074   0.4152   1.0000
   9.250   1.5971   0.02703   0.01976  -0.1073   0.4124   1.0000
   9.500   1.6306   0.02717   0.01981  -0.1084   0.4097   1.0000
   9.750   1.6343   0.02802   0.02091  -0.1050   0.4056   1.0000
  10.000   1.6461   0.02856   0.02158  -0.1028   0.4015   1.0000
  10.250   1.6682   0.02868   0.02173  -0.1020   0.3979   1.0000
  10.500   1.7006   0.02851   0.02150  -0.1027   0.3948   1.0000
  10.750   1.7168   0.02901   0.02209  -0.1012   0.3911   1.0000
  11.000   1.7160   0.02983   0.02311  -0.0972   0.3866   1.0000
  11.250   1.7315   0.03003   0.02337  -0.0955   0.3826   1.0000
  11.500   1.7636   0.02976   0.02306  -0.0961   0.3791   1.0000
  11.750   1.7767   0.03018   0.02356  -0.0941   0.3751   1.0000
  12.000   1.7619   0.03119   0.02476  -0.0881   0.3707   1.0000
  12.250   1.7722   0.03145   0.02508  -0.0857   0.3664   1.0000
  12.500   1.8103   0.03087   0.02442  -0.0871   0.3624   1.0000
  12.750   1.7936   0.03223   0.02598  -0.0816   0.3580   1.0000
  13.000   1.7834   0.03346   0.02736  -0.0774   0.3531   1.0000
  13.250   1.8076   0.03318   0.02705  -0.0769   0.3484   1.0000
  13.500   1.8059   0.03431   0.02828  -0.0741   0.3436   1.0000
  13.750   1.7863   0.03656   0.03070  -0.0703   0.3381   1.0000
  14.000   1.8067   0.03649   0.03061  -0.0696   0.3330   1.0000
  14.250   1.7903   0.03903   0.03331  -0.0669   0.3272   1.0000
  14.500   1.7793   0.04141   0.03580  -0.0649   0.3209   1.0000
  14.750   1.7972   0.04165   0.03600  -0.0642   0.3152   1.0000
  15.000   1.7597   0.04674   0.04130  -0.0622   0.3078   1.0000
  15.250   1.7878   0.04602   0.04049  -0.0617   0.3016   1.0000
  15.500   1.7391   0.05297   0.04768  -0.0605   0.2934   1.0000
  15.750   1.7588   0.05302   0.04766  -0.0600   0.2865   1.0000
  16.000   1.7184   0.05993   0.05476  -0.0598   0.2777   1.0000
  16.250   1.7202   0.06214   0.05697  -0.0595   0.2698   1.0000
  16.500   1.7065   0.06635   0.06123  -0.0596   0.2611   1.0000
  16.750   1.6897   0.07117   0.06612  -0.0600   0.2524   1.0000
  17.000   1.7041   0.07184   0.06668  -0.0596   0.2443   1.0000
  17.250   1.6734   0.07881   0.07380  -0.0606   0.2351   1.0000
  17.500   1.6710   0.08192   0.07690  -0.0609   0.2266   1.0000
  17.750   1.6688   0.08503   0.07998  -0.0612   0.2181   1.0000
  18.000   1.6525   0.09029   0.08533  -0.0622   0.2097   1.0000
  18.250   1.6607   0.09189   0.08681  -0.0622   0.2019   1.0000
  18.500   1.6419   0.09775   0.09281  -0.0636   0.1939   1.0000
  18.750   1.6437   0.10038   0.09539  -0.0640   0.1865   1.0000
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