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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 100,000
Max Cl/Cd: 46.86 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1200-il-100000.txt
Download as CSV file: xf-e1200-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2805   0.10343   0.09889  -0.0689   0.9603   0.1629
  -9.250  -0.3103   0.09778   0.09333  -0.0760   0.9561   0.1719
  -9.000  -0.2936   0.09567   0.09121  -0.0739   0.9525   0.1741
  -8.750  -0.2897   0.09315   0.08870  -0.0735   0.9478   0.1772
  -8.250  -0.5717   0.06248   0.05672  -0.0785   0.9276   0.0805
  -8.000  -0.5594   0.05844   0.05248  -0.0793   0.9252   0.0794
  -7.750  -0.5717   0.05657   0.05048  -0.0748   0.9220   0.0784
  -7.500  -0.5751   0.05383   0.04748  -0.0720   0.9191   0.0770
  -7.250  -0.5703   0.05053   0.04376  -0.0704   0.9161   0.0750
  -7.000  -0.5601   0.04671   0.03922  -0.0693   0.9136   0.0723
  -6.750  -0.5417   0.04425   0.03618  -0.0688   0.9118   0.0713
  -6.500  -0.5148   0.04231   0.03394  -0.0694   0.9099   0.0717
  -6.250  -0.4981   0.04104   0.03249  -0.0682   0.9073   0.0726
  -6.000  -0.4866   0.04014   0.03149  -0.0661   0.9046   0.0741
  -5.750  -0.4704   0.03934   0.03055  -0.0648   0.9027   0.0766
  -5.500  -0.4508   0.03850   0.02951  -0.0638   0.9006   0.0789
  -5.250  -0.4257   0.03766   0.02844  -0.0635   0.8978   0.0810
  -5.000  -0.3962   0.03651   0.02736  -0.0641   0.8951   0.0843
  -4.750  -0.3626   0.03600   0.02686  -0.0653   0.8928   0.0907
  -4.500  -0.3526   0.03557   0.02640  -0.0629   0.8905   0.0958
  -4.250  -0.3412   0.03509   0.02606  -0.0608   0.8877   0.1035
  -4.000  -0.3249   0.03452   0.02561  -0.0595   0.8855   0.1157
  -3.750  -0.3049   0.03374   0.02509  -0.0589   0.8829   0.1488
  -3.500  -0.2776   0.03195   0.02442  -0.0604   0.8795   0.2955
  -3.250  -0.2514   0.03171   0.02574  -0.0595   0.8763   0.5834
  -3.000  -0.2471   0.03258   0.02664  -0.0552   0.8734   0.6420
  -2.750  -0.2408   0.03359   0.02761  -0.0509   0.8701   0.6840
  -2.500  -0.2350   0.03473   0.02879  -0.0457   0.8675   0.7120
  -2.250  -0.2199   0.03571   0.02970  -0.0424   0.8636   0.7369
  -2.000  -0.1940   0.03691   0.03081  -0.0400   0.8586   0.7586
  -1.750  -0.1966   0.03723   0.03111  -0.0349   0.8549   0.7737
  -1.500  -0.1898   0.03772   0.03155  -0.0311   0.8511   0.7899
  -1.250  -0.1742   0.03826   0.03201  -0.0282   0.8465   0.8068
  -1.000  -0.1565   0.03873   0.03240  -0.0256   0.8392   0.8229
  -0.750  -0.1497   0.03894   0.03255  -0.0223   0.8338   0.8369
  -0.500  -0.1212   0.03938   0.03289  -0.0211   0.8271   0.8532
  -0.250  -0.1210   0.03943   0.03291  -0.0166   0.8192   0.8682
   0.000  -0.1093   0.03956   0.03300  -0.0128   0.8128   0.8869
   0.250  -0.0975   0.03963   0.03302  -0.0093   0.8040   0.9054
   0.500  -0.0766   0.03974   0.03306  -0.0080   0.7964   0.9196
   0.750  -0.0513   0.03990   0.03313  -0.0082   0.7868   0.9288
   1.000  -0.0137   0.04016   0.03330  -0.0103   0.7788   0.9354
   1.250   0.0092   0.04036   0.03343  -0.0106   0.7688   0.9427
   1.500   0.0556   0.04067   0.03364  -0.0141   0.7615   0.9476
   1.750   0.0794   0.04097   0.03390  -0.0147   0.7507   0.9544
   2.000   0.1323   0.04117   0.03400  -0.0190   0.7443   0.9586
   2.250   0.1595   0.04163   0.03445  -0.0206   0.7327   0.9646
   2.500   0.2162   0.04163   0.03437  -0.0251   0.7273   0.9686
   2.750   0.2456   0.04212   0.03485  -0.0272   0.7149   0.9741
   3.000   0.3083   0.04188   0.03455  -0.0323   0.7105   0.9774
   3.250   0.3367   0.04234   0.03503  -0.0343   0.6975   0.9839
   3.500   0.4010   0.04176   0.03441  -0.0393   0.6939   0.9865
   3.750   0.4283   0.04219   0.03486  -0.0411   0.6807   0.9953
   4.000   0.4863   0.04133   0.03398  -0.0450   0.6771   1.0000
   4.250   0.4762   0.04132   0.03397  -0.0403   0.6637   1.0000
   4.500   0.4872   0.04149   0.03413  -0.0388   0.6512   1.0000
   4.750   0.5365   0.04043   0.03307  -0.0411   0.6474   1.0000
   5.000   0.5552   0.04065   0.03330  -0.0409   0.6347   1.0000
   5.250   0.6077   0.03927   0.03193  -0.0434   0.6315   1.0000
   5.500   0.6296   0.03941   0.03211  -0.0435   0.6186   1.0000
   5.750   0.6840   0.03766   0.03038  -0.0459   0.6160   1.0000
   7.000   0.9041   0.03005   0.02301  -0.0525   0.5822   1.0000
   7.250   0.9418   0.02886   0.02187  -0.0533   0.5700   1.0000
   7.500   0.9810   0.02761   0.02065  -0.0541   0.5558   1.0000
   7.750   1.0273   0.02610   0.01913  -0.0556   0.5396   1.0000
   8.000   1.0732   0.02486   0.01780  -0.0573   0.5189   1.0000
   8.250   1.1030   0.02463   0.01746  -0.0574   0.4929   1.0000
   8.500   1.1335   0.02464   0.01726  -0.0577   0.4665   1.0000
   8.750   1.1645   0.02485   0.01721  -0.0581   0.4413   1.0000
   9.000   1.1825   0.02565   0.01789  -0.0573   0.4185   1.0000
   9.250   1.2028   0.02644   0.01852  -0.0567   0.3980   1.0000
   9.500   1.2241   0.02725   0.01918  -0.0562   0.3797   1.0000
   9.750   1.2439   0.02814   0.01996  -0.0557   0.3633   1.0000
  10.000   1.2620   0.02909   0.02085  -0.0549   0.3483   1.0000
  10.250   1.2797   0.03008   0.02178  -0.0542   0.3345   1.0000
  10.500   1.2991   0.03105   0.02269  -0.0536   0.3219   1.0000
  10.750   1.3227   0.03196   0.02350  -0.0536   0.3097   1.0000
  11.000   1.3356   0.03305   0.02462  -0.0523   0.2986   1.0000
  11.250   1.3501   0.03420   0.02582  -0.0513   0.2884   1.0000
  11.500   1.3750   0.03515   0.02665  -0.0514   0.2778   1.0000
  11.750   1.3818   0.03642   0.02805  -0.0495   0.2687   1.0000
  12.000   1.4005   0.03758   0.02920  -0.0490   0.2596   1.0000
  12.250   1.4141   0.03873   0.03039  -0.0480   0.2508   1.0000
  12.500   1.4260   0.04011   0.03184  -0.0469   0.2428   1.0000
  12.750   1.4417   0.04125   0.03298  -0.0461   0.2346   1.0000
  13.000   1.4509   0.04279   0.03465  -0.0448   0.2273   1.0000
  13.250   1.4613   0.04411   0.03602  -0.0436   0.2199   1.0000
  13.500   1.4745   0.04561   0.03757  -0.0427   0.2129   1.0000
  13.750   1.4752   0.04736   0.03950  -0.0408   0.2067   1.0000
  14.000   1.4999   0.04847   0.04051  -0.0410   0.1993   1.0000
  14.250   1.4888   0.05081   0.04314  -0.0384   0.1943   1.0000
  14.500   1.5091   0.05183   0.04410  -0.0382   0.1875   1.0000
  14.750   1.5076   0.05416   0.04663  -0.0366   0.1824   1.0000
  15.000   1.4984   0.05671   0.04942  -0.0346   0.1777   1.0000
  15.250   1.5336   0.05719   0.04967  -0.0354   0.1704   1.0000
  15.500   1.5102   0.06067   0.05353  -0.0329   0.1673   1.0000
  15.750   1.4967   0.06384   0.05695  -0.0313   0.1632   1.0000
  16.000   1.5369   0.06375   0.05659  -0.0321   0.1560   1.0000
  16.250   1.5074   0.06809   0.06132  -0.0301   0.1538   1.0000
  16.500   1.4828   0.07259   0.06614  -0.0289   0.1509   1.0000
  16.750   1.4692   0.07637   0.07014  -0.0284   0.1474   1.0000
  17.000   1.5055   0.07606   0.06962  -0.0285   0.1412   1.0000
  17.250   1.4676   0.08226   0.07619  -0.0281   0.1398   1.0000
  17.500   1.4258   0.08972   0.08402  -0.0288   0.1384   1.0000
  17.750   1.3690   0.10008   0.09472  -0.0314   0.1379   1.0000
  18.250   1.3943   0.10298   0.09765  -0.0317   0.1292   1.0000
  18.500   1.3390   0.11454   0.10949  -0.0361   0.1287   1.0000
  18.750   0.9313   0.21753   0.21233  -0.0965   0.1746   1.0000
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