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Dormoy (dormoy-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 500,000
Max Cl/Cd: 64.69 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dormoy-il-500000.txt
Download as CSV file: xf-dormoy-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3223   0.08389   0.08185  -0.0293   1.0000   0.0091
 -10.250  -0.3225   0.08019   0.07818  -0.0300   1.0000   0.0094
 -10.000  -0.3238   0.07637   0.07438  -0.0307   1.0000   0.0097
  -9.750  -0.3264   0.07241   0.07045  -0.0316   1.0000   0.0098
  -9.500  -0.3299   0.06851   0.06657  -0.0324   1.0000   0.0099
  -9.250  -0.3347   0.06471   0.06281  -0.0331   1.0000   0.0104
  -9.000  -0.3422   0.06090   0.05904  -0.0339   1.0000   0.0107
  -8.750  -0.3550   0.05734   0.05554  -0.0343   1.0000   0.0102
  -8.500  -0.3743   0.05425   0.05251  -0.0342   1.0000   0.0099
  -8.250  -0.3733   0.04861   0.04684  -0.0396   0.9972   0.0104
  -8.000  -0.3573   0.04125   0.03936  -0.0478   0.9907   0.0108
  -7.750  -0.3375   0.03449   0.03243  -0.0540   0.9840   0.0112
  -7.500  -0.3145   0.02880   0.02651  -0.0581   0.9759   0.0127
  -7.250  -0.2785   0.02630   0.02369  -0.0610   0.9693   0.0143
  -7.000  -0.2545   0.02246   0.01952  -0.0631   0.9565   0.0144
  -6.750  -0.2303   0.01884   0.01558  -0.0645   0.9424   0.0145
  -6.500  -0.2076   0.01580   0.01220  -0.0650   0.9250   0.0145
  -4.000   0.0234   0.01093   0.00452  -0.0600   0.8094   0.0178
  -3.750   0.0481   0.01040   0.00392  -0.0592   0.7993   0.0208
  -3.500   0.0729   0.00988   0.00329  -0.0583   0.7896   0.0204
  -3.250   0.0981   0.00946   0.00275  -0.0575   0.7793   0.0201
  -3.000   0.1236   0.00913   0.00230  -0.0568   0.7674   0.0213
  -2.750   0.1490   0.00893   0.00193  -0.0560   0.7506   0.0241
  -2.500   0.1746   0.00879   0.00165  -0.0553   0.7313   0.0326
  -2.250   0.1975   0.00819   0.00150  -0.0545   0.7142   0.1923
  -2.000   0.2174   0.00732   0.00140  -0.0534   0.6965   0.4464
  -1.750   0.2305   0.00633   0.00140  -0.0504   0.6753   0.7487
  -1.500   0.2831   0.00616   0.00153  -0.0550   0.6253   0.9629
  -1.250   0.3262   0.00652   0.00152  -0.0583   0.5609   0.9832
  -1.000   0.3658   0.00684   0.00152  -0.0611   0.5011   0.9920
  -0.750   0.4051   0.00736   0.00157  -0.0641   0.4026   0.9993
  -0.500   0.4271   0.00780   0.00167  -0.0633   0.3418   1.0000
  -0.250   0.4487   0.00804   0.00174  -0.0623   0.3159   1.0000
   0.000   0.4711   0.00823   0.00181  -0.0613   0.2953   1.0000
   0.250   0.4934   0.00844   0.00188  -0.0604   0.2697   1.0000
   0.500   0.5116   0.00905   0.00205  -0.0588   0.1784   1.0000
   0.750   0.5332   0.00936   0.00223  -0.0578   0.1583   1.0000
   1.000   0.5563   0.00954   0.00237  -0.0570   0.1488   1.0000
   1.250   0.5795   0.00974   0.00251  -0.0562   0.1405   1.0000
   1.500   0.6003   0.01016   0.00269  -0.0551   0.0825   1.0000
   1.750   0.6216   0.01058   0.00302  -0.0540   0.0625   1.0000
   2.000   0.6450   0.01079   0.00325  -0.0532   0.0586   1.0000
   2.250   0.6684   0.01099   0.00351  -0.0525   0.0549   1.0000
   2.500   0.6914   0.01125   0.00379  -0.0517   0.0504   1.0000
   2.750   0.7150   0.01146   0.00400  -0.0510   0.0470   1.0000
   3.000   0.7396   0.01157   0.00411  -0.0506   0.0440   1.0000
   3.250   0.7630   0.01182   0.00426  -0.0498   0.0232   1.0000
   3.500   0.7860   0.01215   0.00466  -0.0489   0.0163   1.0000
   3.750   0.8088   0.01251   0.00513  -0.0480   0.0150   1.0000
   4.000   0.8311   0.01295   0.00566  -0.0470   0.0143   1.0000
   4.250   0.8516   0.01359   0.00642  -0.0457   0.0125   1.0000
   4.500   0.8702   0.01442   0.00738  -0.0441   0.0114   1.0000
   4.750   0.8854   0.01557   0.00869  -0.0418   0.0108   1.0000
   5.000   0.8986   0.01687   0.01012  -0.0393   0.0106   1.0000
   5.250   0.9141   0.01799   0.01136  -0.0372   0.0108   1.0000
   5.500   0.9328   0.01884   0.01228  -0.0356   0.0114   1.0000
   5.750   0.9524   0.02003   0.01364  -0.0337   0.0146   1.0000
   8.000   1.0745   0.04730   0.04269  -0.0186   0.0102   1.0000
   8.250   1.0739   0.05021   0.04585  -0.0157   0.0102   1.0000
   8.500   1.0702   0.05303   0.04890  -0.0126   0.0101   1.0000
   8.750   1.0624   0.05560   0.05169  -0.0092   0.0101   1.0000
   9.000   1.0502   0.05801   0.05425  -0.0055   0.0101   1.0000
   9.250   1.0368   0.05995   0.05636  -0.0021   0.0100   1.0000
   9.500   1.0237   0.06255   0.05911  -0.0002   0.0099   1.0000
   9.750   1.0298   0.06296   0.05964   0.0011   0.0090   1.0000
  10.000   1.0153   0.06636   0.06319   0.0015   0.0089   1.0000
  10.250   0.9994   0.07034   0.06731   0.0011   0.0088   1.0000
  10.500   0.8592   0.07795   0.07524  -0.0020   0.0102   1.0000
  10.750   0.8382   0.08423   0.08163  -0.0048   0.0102   1.0000
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