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Coanda 1 (coanda1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Coanda 1 (coanda1-il)
Reynolds number: 200,000
Max Cl/Cd: 60.94 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda1-il-200000.txt
Download as CSV file: xf-coanda1-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 1                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3487   0.07964   0.07647  -0.0198   1.0000   0.0465
  -7.750  -0.3491   0.07648   0.07335  -0.0195   1.0000   0.0475
  -7.500  -0.4444   0.08629   0.08304  -0.0186   1.0000   0.0451
  -7.250  -0.4393   0.08311   0.07988  -0.0169   1.0000   0.0460
  -7.000  -0.4358   0.08029   0.07708  -0.0165   1.0000   0.0470
  -6.750  -0.4325   0.07737   0.07418  -0.0166   1.0000   0.0482
  -6.500  -0.4283   0.07442   0.07124  -0.0171   1.0000   0.0495
  -6.250  -0.4229   0.07131   0.06812  -0.0180   1.0000   0.0515
  -6.000  -0.4071   0.06890   0.06552  -0.0243   1.0000   0.0544
  -5.750  -0.3970   0.06586   0.06233  -0.0248   1.0000   0.0546
  -5.500  -0.3879   0.06238   0.05874  -0.0240   1.0000   0.0547
  -5.250  -0.3786   0.05888   0.05514  -0.0228   1.0000   0.0547
  -5.000  -0.3694   0.05513   0.05129  -0.0214   1.0000   0.0547
  -4.750  -0.3768   0.04349   0.03958  -0.0190   1.0000   0.0346
  -4.500  -0.3664   0.04052   0.03649  -0.0168   1.0000   0.0314
  -4.250  -0.3566   0.03602   0.03173  -0.0145   1.0000   0.0292
  -4.000  -0.3567   0.02275   0.01711  -0.0089   1.0000   0.0243
  -3.750  -0.3397   0.01942   0.01310  -0.0063   1.0000   0.0242
  -3.500  -0.3197   0.01729   0.01048  -0.0044   1.0000   0.0257
  -3.250  -0.2988   0.01641   0.00941  -0.0029   1.0000   0.0298
  -3.000  -0.2765   0.01538   0.00809  -0.0013   1.0000   0.0317
  -2.750  -0.2547   0.01482   0.00739   0.0003   1.0000   0.0362
  -2.500  -0.2343   0.01587   0.00873   0.0018   0.9997   0.0491
  -2.250  -0.1878   0.01867   0.01149  -0.0023   0.9915   0.0824
  -2.000  -0.1478   0.01923   0.01205  -0.0056   0.9848   0.0972
  -1.750  -0.1117   0.01954   0.01243  -0.0085   0.9778   0.1252
  -1.250  -0.0351   0.01884   0.01136  -0.0131   0.9647   0.1433
  -1.000   0.0056   0.01753   0.00999  -0.0157   0.9590   0.1383
  -0.750   0.0482   0.01693   0.00910  -0.0182   0.9513   0.1322
  -0.500   0.0948   0.01650   0.00856  -0.0217   0.9440   0.1308
  -0.250   0.1369   0.01552   0.00757  -0.0243   0.9342   0.1318
   0.000   0.1848   0.01492   0.00694  -0.0279   0.9260   0.1306
   0.250   0.2313   0.01407   0.00610  -0.0313   0.9172   0.1306
   0.500   0.2746   0.01330   0.00538  -0.0340   0.9048   0.1308
   1.000   0.3533   0.01201   0.00430  -0.0382   0.8757   0.1339
   1.250   0.3879   0.01161   0.00397  -0.0393   0.8541   0.1356
   1.500   0.4218   0.01129   0.00368  -0.0402   0.8282   0.1375
   1.750   0.4533   0.01108   0.00347  -0.0406   0.7975   0.1406
   2.000   0.4830   0.01099   0.00331  -0.0406   0.7654   0.1440
   2.250   0.5092   0.01094   0.00323  -0.0399   0.7319   0.1473
   2.500   0.5341   0.01102   0.00321  -0.0390   0.6980   0.1507
   2.750   0.5559   0.01119   0.00321  -0.0374   0.6505   0.1558
   3.000   0.5736   0.01147   0.00320  -0.0349   0.5789   0.1638
   3.250   0.7215   0.01184   0.00407  -0.0630   0.3156   1.0000
   3.500   0.7410   0.01246   0.00431  -0.0616   0.2530   1.0000
   3.750   0.7622   0.01296   0.00459  -0.0603   0.2086   1.0000
   4.250   0.8050   0.01396   0.00533  -0.0578   0.1394   1.0000
   4.500   0.8199   0.01531   0.00601  -0.0557   0.0318   1.0000
   4.750   0.8415   0.01588   0.00658  -0.0543   0.0265   1.0000
   5.000   0.8633   0.01645   0.00729  -0.0528   0.0246   1.0000
   5.250   0.8845   0.01710   0.00814  -0.0512   0.0242   1.0000
   5.500   0.9048   0.01784   0.00908  -0.0495   0.0242   1.0000
   5.750   0.9232   0.01877   0.01020  -0.0475   0.0243   1.0000
   6.000   0.9393   0.01992   0.01153  -0.0451   0.0241   1.0000
   6.250   0.9555   0.02111   0.01281  -0.0428   0.0235   1.0000
   6.500   0.9718   0.02253   0.01431  -0.0405   0.0230   1.0000
   6.750   0.9894   0.02443   0.01626  -0.0383   0.0239   1.0000
   7.000   1.0103   0.02658   0.01847  -0.0367   0.0250   1.0000
   7.250   1.0346   0.02752   0.01969  -0.0349   0.0280   1.0000
   7.500   1.0562   0.03131   0.02385  -0.0330   0.0326   1.0000
   7.750   1.0777   0.03418   0.02736  -0.0299   0.0409   1.0000
  10.500   0.7594   0.09388   0.09083  -0.0079   0.0869   1.0000
  10.750   0.7392   0.10160   0.09850  -0.0109   0.0870   1.0000
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