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Dormoy (dormoy-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.12 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dormoy-il-1000000.txt
Download as CSV file: xf-dormoy-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4099   0.10166   0.10007  -0.0217   1.0000   0.0042
 -10.750  -0.4072   0.09788   0.09631  -0.0231   1.0000   0.0042
 -10.500  -0.4049   0.09409   0.09254  -0.0245   1.0000   0.0042
  -7.750  -0.3461   0.04282   0.04096  -0.0618   0.9717   0.0062
  -7.500  -0.3046   0.03918   0.03704  -0.0647   0.9630   0.0077
  -7.250  -0.2716   0.03475   0.03228  -0.0689   0.9456   0.0077
  -7.000  -0.2427   0.03118   0.02831  -0.0712   0.9095   0.0078
  -6.750  -0.2249   0.02894   0.02564  -0.0700   0.8682   0.0078
  -6.500  -0.2085   0.02678   0.02312  -0.0684   0.8440   0.0078
  -6.250  -0.1901   0.02471   0.02073  -0.0671   0.8300   0.0078
  -5.750  -0.1570   0.01729   0.01258  -0.0639   0.8092   0.0089
  -5.500  -0.1336   0.01598   0.01112  -0.0632   0.7993   0.0093
  -5.250  -0.1094   0.01487   0.00983  -0.0624   0.7906   0.0099
  -5.000  -0.0844   0.01388   0.00868  -0.0617   0.7818   0.0106
  -4.750  -0.0586   0.01300   0.00767  -0.0611   0.7734   0.0115
  -4.500  -0.0323   0.01241   0.00696  -0.0604   0.7646   0.0131
  -4.250  -0.0072   0.01023   0.00453  -0.0587   0.7555   0.0087
  -4.000   0.0172   0.00947   0.00374  -0.0579   0.7452   0.0101
  -3.750   0.0424   0.00900   0.00319  -0.0572   0.7337   0.0111
  -3.500   0.0673   0.00863   0.00271  -0.0565   0.7142   0.0119
  -3.250   0.0918   0.00843   0.00237  -0.0557   0.6836   0.0132
  -3.000   0.1160   0.00818   0.00191  -0.0548   0.6481   0.0133
  -2.750   0.1403   0.00807   0.00159  -0.0539   0.6097   0.0141
  -2.500   0.1650   0.00800   0.00128  -0.0532   0.5723   0.0163
  -2.250   0.1894   0.00811   0.00111  -0.0525   0.5204   0.0193
  -2.000   0.2117   0.00796   0.00101  -0.0515   0.4595   0.1347
  -1.750   0.2331   0.00822   0.00108  -0.0506   0.3655   0.1940
  -1.500   0.2540   0.00785   0.00111  -0.0497   0.3277   0.3873
  -1.250   0.2753   0.00742   0.00114  -0.0487   0.3061   0.5672
  -1.000   0.2905   0.00676   0.00122  -0.0461   0.2915   0.8152
  -0.750   0.3247   0.00665   0.00135  -0.0473   0.2653   0.9531
  -0.500   0.3634   0.00731   0.00155  -0.0502   0.1635   0.9716
  -0.250   0.4005   0.00751   0.00166  -0.0524   0.1492   0.9828
   0.000   0.4380   0.00769   0.00174  -0.0547   0.1371   0.9889
   0.250   0.4710   0.00816   0.00192  -0.0562   0.0694   0.9947
   0.500   0.5101   0.00833   0.00202  -0.0590   0.0587   0.9985
   0.750   0.5421   0.00846   0.00216  -0.0601   0.0565   1.0000
   1.000   0.5650   0.00863   0.00232  -0.0592   0.0530   1.0000
   1.250   0.5876   0.00884   0.00255  -0.0582   0.0482   1.0000
   1.500   0.6110   0.00899   0.00270  -0.0575   0.0471   1.0000
   1.750   0.6353   0.00906   0.00272  -0.0569   0.0460   1.0000
   2.000   0.6594   0.00917   0.00281  -0.0563   0.0441   1.0000
   2.250   0.6834   0.00929   0.00290  -0.0557   0.0401   1.0000
   2.500   0.7072   0.00944   0.00301  -0.0550   0.0341   1.0000
   2.750   0.7292   0.00979   0.00325  -0.0540   0.0137   1.0000
   3.000   0.7528   0.01001   0.00353  -0.0532   0.0118   1.0000
   3.250   0.7760   0.01029   0.00391  -0.0523   0.0100   1.0000
   3.500   0.7988   0.01061   0.00431  -0.0514   0.0095   1.0000
   3.750   0.8212   0.01096   0.00471  -0.0505   0.0087   1.0000
   4.000   0.8430   0.01139   0.00521  -0.0494   0.0081   1.0000
   4.250   0.8641   0.01189   0.00578  -0.0482   0.0073   1.0000
   4.500   0.8838   0.01253   0.00649  -0.0468   0.0065   1.0000
   4.750   0.8998   0.01353   0.00758  -0.0447   0.0058   1.0000
   5.000   0.9140   0.01467   0.00884  -0.0424   0.0057   1.0000
   5.250   0.9307   0.01561   0.00986  -0.0404   0.0058   1.0000
   5.500   0.9100   0.00874   0.00349  -0.0332   0.0102   1.0000
   5.750   0.9321   0.01041   0.00525  -0.0324   0.0102   1.0000
   6.000   0.9530   0.01192   0.00688  -0.0314   0.0101   1.0000
   6.250   0.9716   0.01020   0.00522  -0.0301   0.0082   1.0000
   6.500   0.9900   0.01121   0.00629  -0.0291   0.0072   1.0000
   6.750   1.0080   0.01273   0.00790  -0.0280   0.0067   1.0000
   7.000   1.0250   0.01436   0.00958  -0.0270   0.0062   1.0000
   7.250   1.0405   0.01735   0.01267  -0.0261   0.0056   1.0000
   7.750   1.0824   0.03945   0.03523  -0.0232   0.0051   1.0000
   8.000   1.0843   0.04229   0.03833  -0.0201   0.0051   1.0000
   8.250   1.0841   0.04501   0.04128  -0.0170   0.0051   1.0000
   8.500   1.0807   0.04759   0.04408  -0.0137   0.0051   1.0000
   8.750   1.0725   0.04979   0.04647  -0.0099   0.0050   1.0000
   9.000   1.0601   0.05217   0.04899  -0.0058   0.0051   1.0000
   9.250   1.0824   0.05101   0.04795  -0.0040   0.0043   1.0000
   9.500   1.0727   0.05374   0.05083  -0.0012   0.0042   1.0000
   9.750   1.0620   0.05667   0.05391   0.0009   0.0040   1.0000
  10.000   1.0457   0.06007   0.05745   0.0021   0.0040   1.0000
  10.250   1.0310   0.06374   0.06125   0.0024   0.0038   1.0000
  10.500   1.0107   0.06831   0.06596   0.0016   0.0040   1.0000
  10.750   0.9950   0.07300   0.07077   0.0000   0.0037   1.0000
  11.000   0.9739   0.07887   0.07676  -0.0029   0.0040   1.0000
  11.250   0.9546   0.08525   0.08326  -0.0066   0.0040   1.0000
  11.500   0.9310   0.09309   0.09121  -0.0117   0.0042   1.0000
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