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Dormoy (dormoy-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 200,000
Max Cl/Cd: 57.43 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dormoy-il-200000.txt
Download as CSV file: xf-dormoy-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dormoy                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4093   0.08759   0.08440  -0.0356   1.0000   0.0258
  -9.500  -0.4076   0.08424   0.08101  -0.0309   1.0000   0.0285
  -9.250  -0.4089   0.08128   0.07811  -0.0313   1.0000   0.0295
  -9.000  -0.4151   0.07818   0.07509  -0.0320   1.0000   0.0302
  -8.750  -0.4204   0.07480   0.07176  -0.0335   1.0000   0.0305
  -8.500  -0.4225   0.07104   0.06803  -0.0355   1.0000   0.0309
  -8.250  -0.4241   0.06717   0.06417  -0.0372   1.0000   0.0318
  -8.000  -0.4250   0.06341   0.06039  -0.0381   1.0000   0.0327
  -7.750  -0.4262   0.05985   0.05680  -0.0382   1.0000   0.0337
  -7.500  -0.4301   0.05667   0.05355  -0.0371   1.0000   0.0349
  -7.250  -0.4355   0.05412   0.05086  -0.0349   1.0000   0.0362
  -6.250  -0.3312   0.03692   0.03270  -0.0483   0.9796   0.0565
  -6.000  -0.2990   0.03378   0.02927  -0.0511   0.9725   0.0691
  -5.750  -0.2662   0.03135   0.02655  -0.0540   0.9664   0.0932
  -4.750  -0.1100   0.01908   0.01191  -0.0570   0.9443   0.0398
  -4.500  -0.0703   0.01718   0.00987  -0.0582   0.9384   0.0344
  -4.250  -0.0324   0.01593   0.00849  -0.0595   0.9311   0.0365
  -4.000   0.0008   0.01447   0.00702  -0.0599   0.9224   0.0352
  -3.750   0.0361   0.01339   0.00587  -0.0609   0.9143   0.0348
  -3.500   0.0665   0.01272   0.00506  -0.0609   0.9031   0.0355
  -3.250   0.0967   0.01222   0.00439  -0.0609   0.8915   0.0382
  -3.000   0.1237   0.01135   0.00381  -0.0604   0.8790   0.1352
  -2.750   0.1446   0.01009   0.00358  -0.0593   0.8662   0.4241
  -2.500   0.2090   0.00861   0.00366  -0.0649   0.8567   0.9584
  -2.250   0.2892   0.00857   0.00335  -0.0756   0.8442   1.0000
  -2.000   0.3117   0.00859   0.00321  -0.0744   0.8281   1.0000
  -1.750   0.3336   0.00864   0.00307  -0.0730   0.8095   1.0000
  -1.500   0.3552   0.00869   0.00295  -0.0715   0.7900   1.0000
  -1.250   0.3763   0.00873   0.00285  -0.0700   0.7689   1.0000
  -1.000   0.3987   0.00878   0.00279  -0.0688   0.7528   1.0000
  -0.750   0.4210   0.00882   0.00275  -0.0676   0.7353   1.0000
  -0.500   0.4434   0.00886   0.00272  -0.0664   0.7165   1.0000
  -0.250   0.4656   0.00891   0.00267  -0.0652   0.6945   1.0000
   0.000   0.4875   0.00899   0.00261  -0.0639   0.6665   1.0000
   0.250   0.5082   0.00913   0.00254  -0.0623   0.6268   1.0000
   0.500   0.5289   0.00933   0.00253  -0.0608   0.5844   1.0000
   0.750   0.5491   0.00961   0.00260  -0.0592   0.5376   1.0000
   1.000   0.5694   0.00992   0.00269  -0.0578   0.4908   1.0000
   1.250   0.5896   0.01027   0.00281  -0.0564   0.4439   1.0000
   1.500   0.6096   0.01067   0.00298  -0.0550   0.4000   1.0000
   1.750   0.6304   0.01105   0.00319  -0.0539   0.3692   1.0000
   2.000   0.6524   0.01136   0.00342  -0.0529   0.3484   1.0000
   2.250   0.6728   0.01181   0.00374  -0.0517   0.3173   1.0000
   2.500   0.6934   0.01227   0.00400  -0.0507   0.2746   1.0000
   2.750   0.7151   0.01266   0.00423  -0.0498   0.2272   1.0000
   3.000   0.7316   0.01358   0.00468  -0.0482   0.1657   1.0000
   3.250   0.7534   0.01403   0.00509  -0.0473   0.1489   1.0000
   3.500   0.7763   0.01439   0.00551  -0.0466   0.1310   1.0000
   3.750   0.7932   0.01539   0.00624  -0.0450   0.0638   1.0000
   4.000   0.8133   0.01609   0.00704  -0.0437   0.0485   1.0000
   4.250   0.8362   0.01650   0.00759  -0.0428   0.0368   1.0000
   4.500   0.8582   0.01704   0.00818  -0.0417   0.0275   1.0000
   4.750   0.8784   0.01780   0.00906  -0.0403   0.0250   1.0000
   5.000   0.8965   0.01876   0.01024  -0.0386   0.0241   1.0000
   5.250   0.9129   0.01976   0.01144  -0.0367   0.0222   1.0000
   5.500   0.9257   0.02101   0.01277  -0.0345   0.0198   1.0000
   5.750   0.9373   0.02242   0.01426  -0.0320   0.0198   1.0000
   6.000   0.9499   0.02417   0.01607  -0.0296   0.0198   1.0000
   6.250   0.9696   0.02640   0.01834  -0.0280   0.0207   1.0000
   6.500   1.0041   0.03018   0.02219  -0.0283   0.0235   1.0000
  12.500   0.6900   0.14549   0.14246  -0.0381   0.0554   1.0000
  12.750   0.6853   0.15012   0.14709  -0.0408   0.0540   1.0000
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