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EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 407 AIRFOIL (e407-il)
Reynolds number: 200,000
Max Cl/Cd: 72.03 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e407-il-200000.txt
Download as CSV file: xf-e407-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 407 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4151   0.09513   0.09226  -0.0460   0.9911   0.0540
  -9.250  -0.4267   0.08784   0.08499  -0.0500   0.9887   0.0546
  -9.000  -0.4519   0.07766   0.07480  -0.0566   0.9865   0.0551
  -8.750  -0.4819   0.06921   0.06629  -0.0619   0.9843   0.0550
  -8.500  -0.5114   0.06360   0.06059  -0.0640   0.9797   0.0547
  -8.250  -0.5444   0.05940   0.05630  -0.0640   0.9745   0.0546
  -8.000  -0.5640   0.05457   0.05129  -0.0669   0.9708   0.0548
  -7.750  -0.6621   0.04949   0.04471  -0.0657   0.9731   0.0244
  -7.500  -0.6440   0.04096   0.03497  -0.0685   0.9709   0.0194
  -7.250  -0.6253   0.03942   0.03313  -0.0680   0.9664   0.0190
  -7.000  -0.6010   0.03674   0.03010  -0.0688   0.9632   0.0189
  -6.750  -0.5744   0.03292   0.02586  -0.0698   0.9610   0.0194
  -6.500  -0.5444   0.03080   0.02354  -0.0708   0.9591   0.0198
  -6.250  -0.5096   0.02998   0.02272  -0.0734   0.9574   0.0231
  -6.000  -0.4921   0.02900   0.02163  -0.0719   0.9522   0.0251
  -5.750  -0.4638   0.02816   0.02066  -0.0723   0.9492   0.0265
  -5.500  -0.4333   0.02621   0.01874  -0.0738   0.9472   0.0315
  -5.250  -0.3955   0.02514   0.01767  -0.0768   0.9454   0.0419
  -5.000  -0.3517   0.02388   0.01648  -0.0813   0.9441   0.0685
  -4.750  -0.3240   0.02230   0.01537  -0.0833   0.9398   0.1427
  -4.500  -0.2746   0.02011   0.01489  -0.0910   0.9392   0.4739
  -4.250  -0.2447   0.02049   0.01531  -0.0913   0.9355   0.5461
  -4.000  -0.2114   0.02115   0.01590  -0.0920   0.9327   0.5780
  -3.750  -0.1835   0.02190   0.01658  -0.0916   0.9291   0.6002
  -3.500  -0.1645   0.02242   0.01706  -0.0896   0.9232   0.6150
  -3.250  -0.1352   0.02307   0.01765  -0.0892   0.9199   0.6267
  -3.000  -0.1007   0.02373   0.01825  -0.0899   0.9177   0.6377
  -2.750  -0.0849   0.02396   0.01839  -0.0879   0.9106   0.6478
  -2.500  -0.0585   0.02446   0.01889  -0.0869   0.9068   0.6545
  -2.250  -0.0220   0.02478   0.01911  -0.0884   0.9045   0.6638
  -2.000  -0.0086   0.02511   0.01945  -0.0854   0.8974   0.6695
  -1.750   0.0236   0.02527   0.01954  -0.0864   0.8936   0.6780
  -1.500   0.0552   0.02557   0.01982  -0.0864   0.8911   0.6841
  -1.250   0.0785   0.02568   0.01986  -0.0862   0.8848   0.6918
  -1.000   0.1054   0.02576   0.01993  -0.0858   0.8801   0.6953
  -0.750   0.1436   0.02570   0.01981  -0.0880   0.8777   0.6994
  -0.500   0.1904   0.02550   0.01950  -0.0925   0.8762   0.7049
  -0.250   0.2037   0.02556   0.01958  -0.0900   0.8671   0.7072
   0.000   0.2404   0.02541   0.01942  -0.0916   0.8642   0.7099
   0.250   0.2822   0.02519   0.01917  -0.0944   0.8625   0.7133
   0.500   0.3038   0.02523   0.01917  -0.0942   0.8536   0.7178
   0.750   0.3436   0.02493   0.01886  -0.0966   0.8508   0.7206
   1.000   0.3831   0.02461   0.01857  -0.0985   0.8489   0.7230
   1.250   0.4021   0.02467   0.01865  -0.0973   0.8397   0.7261
   1.500   0.4431   0.02428   0.01827  -0.0998   0.8370   0.7295
   1.750   0.4909   0.02375   0.01773  -0.1038   0.8353   0.7335
   2.000   0.5101   0.02371   0.01774  -0.1023   0.8260   0.7359
   2.250   0.5504   0.02312   0.01721  -0.1042   0.8232   0.7384
   2.500   0.5944   0.02243   0.01658  -0.1069   0.8215   0.7412
   2.750   0.6195   0.02229   0.01648  -0.1067   0.8123   0.7449
   3.000   0.6648   0.02149   0.01574  -0.1097   0.8097   0.7484
   3.250   0.7089   0.02049   0.01484  -0.1120   0.8081   0.7507
   3.500   0.7529   0.01951   0.01395  -0.1144   0.8055   0.7532
   3.750   0.7795   0.01908   0.01361  -0.1139   0.7959   0.7565
   4.000   0.8316   0.01794   0.01256  -0.1179   0.7933   0.7602
   4.250   0.8586   0.01753   0.01223  -0.1175   0.7823   0.7633
   4.500   0.8907   0.01690   0.01172  -0.1178   0.7719   0.7658
   4.750   0.9265   0.01622   0.01114  -0.1187   0.7601   0.7688
   5.000   0.9579   0.01577   0.01076  -0.1190   0.7436   0.7724
   5.250   0.9986   0.01524   0.01025  -0.1212   0.7231   0.7764
   5.500   1.0262   0.01497   0.01003  -0.1207   0.6955   0.7790
   5.750   1.0541   0.01487   0.00987  -0.1203   0.6599   0.7819
   6.000   1.0798   0.01499   0.00984  -0.1197   0.6158   0.7853
   6.250   1.0991   0.01542   0.01003  -0.1181   0.5657   0.7894
   6.500   1.1106   0.01601   0.01040  -0.1150   0.5181   0.7929
   6.750   1.1178   0.01671   0.01093  -0.1113   0.4710   0.7963
   7.000   1.1247   0.01752   0.01153  -0.1078   0.4240   0.8002
   7.250   1.1321   0.01846   0.01223  -0.1047   0.3767   0.8043
   7.500   1.1382   0.01936   0.01296  -0.1013   0.3334   0.8078
   7.750   1.1452   0.02032   0.01375  -0.0982   0.2917   0.8118
   8.000   1.1541   0.02137   0.01462  -0.0956   0.2506   0.8163
   8.250   1.1633   0.02250   0.01555  -0.0933   0.2105   0.8204
   8.500   1.1708   0.02366   0.01654  -0.0906   0.1747   0.8241
   8.750   1.1807   0.02485   0.01762  -0.0885   0.1415   0.8285
   9.000   1.1910   0.02621   0.01882  -0.0866   0.1127   0.8333
   9.250   1.1973   0.02763   0.02013  -0.0839   0.0917   0.8376
   9.500   1.2063   0.02903   0.02151  -0.0817   0.0746   0.8425
   9.750   1.2155   0.03062   0.02308  -0.0798   0.0624   0.8477
  10.000   1.2197   0.03240   0.02486  -0.0771   0.0546   0.8521
  10.250   1.2314   0.03370   0.02629  -0.0754   0.0480   0.8576
  10.500   1.2379   0.03572   0.02832  -0.0734   0.0429   0.8630
  10.750   1.2488   0.03708   0.02984  -0.0716   0.0389   0.8691
  11.000   1.2581   0.03886   0.03165  -0.0701   0.0353   0.8760
  11.250   1.2673   0.04082   0.03377  -0.0682   0.0321   0.8823
  11.500   1.2792   0.04244   0.03556  -0.0668   0.0294   0.8903
  11.750   1.2865   0.04404   0.03725  -0.0649   0.0270   0.8992
  12.000   1.2970   0.04678   0.04008  -0.0635   0.0242   0.9080
  12.250   1.3017   0.04829   0.04185  -0.0612   0.0228   0.9245
  12.500   1.3040   0.04997   0.04377  -0.0585   0.0215   1.0000
  12.750   1.3147   0.05264   0.04661  -0.0581   0.0201   1.0000
  13.000   1.3223   0.05532   0.04938  -0.0578   0.0188   1.0000
  13.250   1.3257   0.06056   0.05486  -0.0571   0.0173   1.0000
  13.500   1.3227   0.06335   0.05793  -0.0564   0.0167   1.0000
  13.750   1.3191   0.06689   0.06174  -0.0559   0.0161   1.0000
  14.000   1.3129   0.07106   0.06619  -0.0555   0.0156   1.0000
  14.250   1.3033   0.07584   0.07125  -0.0555   0.0153   1.0000
  14.500   1.2910   0.08110   0.07678  -0.0560   0.0150   1.0000
  14.750   1.2761   0.08690   0.08286  -0.0570   0.0149   1.0000
  15.000   1.2591   0.09328   0.08951  -0.0589   0.0149   1.0000
  15.250   1.2402   0.10034   0.09683  -0.0617   0.0149   1.0000
  15.500   1.2197   0.10812   0.10486  -0.0655   0.0150   1.0000
  15.750   1.1981   0.11667   0.11365  -0.0703   0.0151   1.0000
  16.000   1.1756   0.12611   0.12331  -0.0763   0.0154   1.0000
  16.250   1.1525   0.13649   0.13389  -0.0834   0.0157   1.0000
  16.500   1.1287   0.14798   0.14555  -0.0916   0.0161   1.0000
  16.750   1.1026   0.16120   0.15889  -0.1010   0.0166   1.0000
  17.000   1.0781   0.17470   0.17244  -0.1097   0.0173   1.0000
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