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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 50,000
Max Cl/Cd: 23.44 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1200-il-50000-n5.txt
Download as CSV file: xf-e1200-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1200 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3308   0.13751   0.13045  -0.0530   1.0000   0.0645
 -12.500  -0.3443   0.13545   0.12850  -0.0512   1.0000   0.0632
 -12.000  -0.3760   0.12473   0.11790  -0.0554   0.9964   0.0591
 -11.750  -0.3680   0.11985   0.11302  -0.0589   0.9916   0.0587
 -11.500  -0.3640   0.11455   0.10772  -0.0627   0.9865   0.0584
 -11.000  -0.3702   0.10145   0.09462  -0.0722   0.9760   0.0582
 -10.750  -0.3791   0.09348   0.08663  -0.0783   0.9708   0.0577
 -10.500  -0.3986   0.08570   0.07879  -0.0842   0.9638   0.0572
 -10.250  -0.4235   0.07824   0.07119  -0.0902   0.9570   0.0567
 -10.000  -0.4501   0.07320   0.06600  -0.0926   0.9483   0.0563
  -9.750  -0.4711   0.06885   0.06143  -0.0946   0.9414   0.0560
  -9.500  -0.4963   0.06625   0.05867  -0.0925   0.9319   0.0559
  -9.250  -0.5060   0.06253   0.05462  -0.0929   0.9258   0.0562
  -9.000  -0.5212   0.06019   0.05203  -0.0900   0.9178   0.0566
  -8.750  -0.5236   0.05727   0.04874  -0.0890   0.9124   0.0571
  -8.500  -0.5192   0.05427   0.04528  -0.0885   0.9083   0.0580
  -8.250  -0.5233   0.05243   0.04314  -0.0853   0.9015   0.0584
  -8.000  -0.5131   0.05001   0.04026  -0.0843   0.8972   0.0591
  -7.750  -0.4926   0.04794   0.03800  -0.0844   0.8942   0.0602
  -7.500  -0.4762   0.04648   0.03640  -0.0836   0.8908   0.0616
  -7.250  -0.4686   0.04547   0.03527  -0.0812   0.8856   0.0632
  -7.000  -0.4504   0.04421   0.03379  -0.0803   0.8818   0.0662
  -6.750  -0.4257   0.04285   0.03207  -0.0802   0.8788   0.0694
  -6.500  -0.3980   0.04166   0.03089  -0.0805   0.8766   0.0725
  -6.250  -0.3867   0.04104   0.03021  -0.0780   0.8724   0.0751
  -6.000  -0.3714   0.04041   0.02945  -0.0760   0.8681   0.0792
  -5.750  -0.3505   0.03970   0.02872  -0.0751   0.8647   0.0851
  -5.500  -0.3266   0.03902   0.02791  -0.0745   0.8618   0.0937
  -5.250  -0.3026   0.03820   0.02715  -0.0744   0.8595   0.1046
  -5.000  -0.3012   0.03784   0.02684  -0.0707   0.8541   0.1143
  -4.750  -0.2886   0.03718   0.02627  -0.0690   0.8498   0.1339
  -4.500  -0.2709   0.03630   0.02560  -0.0683   0.8464   0.1679
  -4.250  -0.2510   0.03514   0.02489  -0.0685   0.8437   0.2310
  -4.000  -0.2421   0.03413   0.02451  -0.0668   0.8396   0.3183
  -3.750  -0.2383   0.03372   0.02505  -0.0628   0.8347   0.4419
  -3.500  -0.2267   0.03457   0.02636  -0.0578   0.8308   0.5582
  -3.250  -0.2047   0.03535   0.02695  -0.0559   0.8276   0.6242
  -3.000  -0.1886   0.03610   0.02752  -0.0532   0.8238   0.6628
  -2.750  -0.1822   0.03679   0.02811  -0.0491   0.8184   0.6882
  -2.500  -0.1664   0.03742   0.02860  -0.0461   0.8142   0.7124
  -2.250  -0.1454   0.03794   0.02893  -0.0440   0.8109   0.7358
  -2.000  -0.1322   0.03845   0.02933  -0.0407   0.8066   0.7546
  -1.750  -0.1258   0.03888   0.02969  -0.0367   0.8010   0.7722
  -1.500  -0.1098   0.03926   0.02995  -0.0338   0.7967   0.7917
  -1.250  -0.0879   0.03955   0.03010  -0.0317   0.7934   0.8115
  -1.000  -0.0819   0.03982   0.03031  -0.0281   0.7876   0.8274
  -0.750  -0.0673   0.03999   0.03037  -0.0259   0.7821   0.8412
  -0.500  -0.0421   0.04007   0.03030  -0.0257   0.7781   0.8525
  -0.250  -0.0205   0.04022   0.03031  -0.0251   0.7736   0.8618
   0.000  -0.0088   0.04038   0.03040  -0.0233   0.7667   0.8704
   0.250   0.0184   0.04049   0.03038  -0.0237   0.7622   0.8780
   0.500   0.0471   0.04061   0.03038  -0.0244   0.7580   0.8849
   0.750   0.0576   0.04089   0.03060  -0.0227   0.7500   0.8927
   1.000   0.0875   0.04101   0.03062  -0.0237   0.7453   0.8993
   1.250   0.1105   0.04127   0.03081  -0.0238   0.7392   0.9060
   1.500   0.1304   0.04152   0.03101  -0.0235   0.7318   0.9136
   1.750   0.1675   0.04166   0.03107  -0.0255   0.7275   0.9193
   2.000   0.1816   0.04208   0.03147  -0.0247   0.7185   0.9279
   2.250   0.2175   0.04228   0.03161  -0.0266   0.7128   0.9339
   2.500   0.2424   0.04264   0.03195  -0.0273   0.7051   0.9420
   2.750   0.2758   0.04294   0.03224  -0.0292   0.6977   0.9488
   3.000   0.3201   0.04293   0.03219  -0.0321   0.6936   0.9556
   3.250   0.3410   0.04358   0.03287  -0.0330   0.6819   0.9653
   3.750   0.4069   0.04392   0.03323  -0.0367   0.6649   0.9928
   4.000   0.4218   0.04424   0.03354  -0.0360   0.6545   1.0000
   4.250   0.4539   0.04408   0.03336  -0.0369   0.6477   1.0000
   4.500   0.4688   0.04455   0.03383  -0.0364   0.6356   1.0000
   4.750   0.5093   0.04408   0.03335  -0.0380   0.6304   1.0000
   5.000   0.5246   0.04463   0.03392  -0.0376   0.6172   1.0000
   5.250   0.5438   0.04509   0.03440  -0.0375   0.6048   1.0000
   5.500   0.5797   0.04469   0.03401  -0.0385   0.5977   1.0000
   5.750   0.6018   0.04498   0.03433  -0.0386   0.5855   1.0000
   6.000   0.6214   0.04545   0.03483  -0.0384   0.5724   1.0000
   6.250   0.6446   0.04570   0.03511  -0.0385   0.5604   1.0000
   6.500   0.6814   0.04494   0.03439  -0.0391   0.5531   1.0000
   6.750   0.7007   0.04538   0.03488  -0.0388   0.5394   1.0000
   7.000   0.7221   0.04565   0.03519  -0.0385   0.5265   1.0000
   7.500   0.7819   0.04471   0.03435  -0.0385   0.5063   1.0000
   7.750   0.8036   0.04493   0.03461  -0.0381   0.4925   1.0000
   8.000   0.8279   0.04495   0.03468  -0.0378   0.4794   1.0000
   8.250   0.8570   0.04453   0.03429  -0.0375   0.4674   1.0000
   8.500   0.8945   0.04339   0.03316  -0.0376   0.4571   1.0000
   8.750   0.9188   0.04346   0.03325  -0.0372   0.4423   1.0000
   9.000   0.9434   0.04356   0.03335  -0.0368   0.4275   1.0000
   9.250   0.9679   0.04372   0.03349  -0.0364   0.4128   1.0000
   9.500   0.9915   0.04400   0.03375  -0.0359   0.3981   1.0000
   9.750   1.0140   0.04442   0.03414  -0.0355   0.3838   1.0000
  10.000   1.0362   0.04492   0.03460  -0.0350   0.3702   1.0000
  10.250   1.0588   0.04540   0.03505  -0.0346   0.3570   1.0000
  10.500   1.0799   0.04607   0.03570  -0.0342   0.3446   1.0000
  10.750   1.0921   0.04749   0.03717  -0.0335   0.3321   1.0000
  11.000   1.1079   0.04864   0.03834  -0.0329   0.3206   1.0000
  11.250   1.1315   0.04920   0.03886  -0.0326   0.3103   1.0000
  11.500   1.1404   0.05095   0.04072  -0.0319   0.2996   1.0000
  11.750   1.1546   0.05231   0.04213  -0.0314   0.2898   1.0000
  12.000   1.1748   0.05316   0.04298  -0.0310   0.2805   1.0000
  12.250   1.1796   0.05537   0.04536  -0.0303   0.2716   1.0000
  12.500   1.2049   0.05582   0.04574  -0.0301   0.2631   1.0000
  12.750   1.2013   0.05876   0.04893  -0.0293   0.2549   1.0000
  13.000   1.2273   0.05917   0.04927  -0.0291   0.2471   1.0000
  13.250   1.2184   0.06268   0.05306  -0.0283   0.2398   1.0000
  13.500   1.2423   0.06318   0.05354  -0.0280   0.2323   1.0000
  13.750   1.2302   0.06717   0.05781  -0.0274   0.2260   1.0000
  14.000   1.2381   0.06923   0.05996  -0.0271   0.2194   1.0000
  14.250   1.2420   0.07176   0.06261  -0.0268   0.2133   1.0000
  14.500   1.2258   0.07654   0.06764  -0.0268   0.2075   1.0000
  14.750   1.2568   0.07605   0.06708  -0.0264   0.2011   1.0000
  15.000   1.2175   0.08388   0.07526  -0.0273   0.1967   1.0000
  15.250   1.1836   0.09180   0.08342  -0.0290   0.1917   1.0000
  15.500   1.2398   0.08739   0.07889  -0.0271   0.1856   1.0000
  15.750   1.0431   0.12396   0.11593  -0.0421   0.1781   1.0000
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