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Falcon (falcon-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 100,000
Max Cl/Cd: 44.33 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-falcon-il-100000-n5.txt
Download as CSV file: xf-falcon-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Falcon                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6225   0.09077   0.08542  -0.0293   1.0000   0.0366
 -11.500  -0.6777   0.07434   0.06887  -0.0411   1.0000   0.0354
 -11.250  -0.7220   0.06518   0.05949  -0.0463   1.0000   0.0348
 -11.000  -0.7546   0.05954   0.05362  -0.0467   1.0000   0.0346
 -10.750  -0.7798   0.05560   0.04945  -0.0445   1.0000   0.0348
 -10.500  -0.8005   0.05238   0.04600  -0.0407   1.0000   0.0351
 -10.250  -0.8141   0.04910   0.04240  -0.0372   1.0000   0.0357
 -10.000  -0.8230   0.04585   0.03878  -0.0337   1.0000   0.0363
  -9.750  -0.8268   0.04272   0.03523  -0.0303   1.0000   0.0370
  -9.500  -0.8255   0.03984   0.03189  -0.0272   1.0000   0.0377
  -9.250  -0.8171   0.03761   0.02942  -0.0248   1.0000   0.0384
  -9.000  -0.8040   0.03624   0.02800  -0.0230   1.0000   0.0394
  -8.750  -0.7905   0.03503   0.02669  -0.0211   1.0000   0.0408
  -8.500  -0.7768   0.03360   0.02506  -0.0191   1.0000   0.0426
  -8.250  -0.7621   0.03195   0.02312  -0.0171   1.0000   0.0443
  -8.000  -0.7457   0.03032   0.02119  -0.0152   1.0000   0.0458
  -7.750  -0.7289   0.02906   0.01995  -0.0136   1.0000   0.0473
  -7.500  -0.7121   0.02815   0.01902  -0.0119   1.0000   0.0493
  -7.250  -0.6949   0.02721   0.01797  -0.0102   1.0000   0.0521
  -7.000  -0.6768   0.02619   0.01673  -0.0084   1.0000   0.0549
  -6.750  -0.6607   0.02526   0.01587  -0.0066   1.0000   0.0573
  -6.500  -0.6444   0.02452   0.01512  -0.0046   1.0000   0.0603
  -6.250  -0.6276   0.02382   0.01430  -0.0027   1.0000   0.0646
  -6.000  -0.6126   0.02314   0.01366  -0.0006   1.0000   0.0685
  -5.750  -0.5971   0.02258   0.01308   0.0015   1.0000   0.0733
  -5.500  -0.5775   0.02195   0.01244   0.0027   0.9988   0.0794
  -5.250  -0.5408   0.02124   0.01169   0.0005   0.9902   0.0893
  -5.000  -0.5062   0.02054   0.01103  -0.0014   0.9799   0.1005
  -4.750  -0.4704   0.01988   0.01039  -0.0033   0.9706   0.1137
  -4.500  -0.4336   0.01925   0.00977  -0.0054   0.9619   0.1292
  -4.250  -0.3940   0.01861   0.00914  -0.0081   0.9546   0.1481
  -4.000  -0.3577   0.01796   0.00855  -0.0100   0.9445   0.1693
  -3.500  -0.2929   0.01617   0.00742  -0.0127   0.9210   0.2794
  -3.250  -0.2680   0.01516   0.00717  -0.0122   0.9065   0.4497
  -3.000  -0.2405   0.01465   0.00700  -0.0118   0.8911   0.5453
  -2.750  -0.2119   0.01432   0.00692  -0.0113   0.8748   0.6201
  -2.500  -0.1814   0.01413   0.00688  -0.0111   0.8578   0.6793
  -2.250  -0.1498   0.01405   0.00683  -0.0110   0.8400   0.7251
  -2.000  -0.1184   0.01401   0.00677  -0.0110   0.8213   0.7632
  -1.750  -0.0857   0.01402   0.00671  -0.0111   0.8024   0.7945
  -1.500  -0.0511   0.01407   0.00667  -0.0117   0.7832   0.8219
  -1.250  -0.0178   0.01416   0.00665  -0.0120   0.7632   0.8483
  -1.000   0.0205   0.01434   0.00671  -0.0133   0.7428   0.8717
  -0.750   0.0578   0.01449   0.00672  -0.0145   0.7227   0.8900
  -0.500   0.0940   0.01459   0.00665  -0.0159   0.7031   0.9018
  -0.250   0.1275   0.01468   0.00657  -0.0168   0.6845   0.9135
   0.000   0.1656   0.01480   0.00654  -0.0187   0.6655   0.9223
   0.250   0.2021   0.01491   0.00650  -0.0204   0.6474   0.9314
   0.500   0.2383   0.01503   0.00649  -0.0220   0.6300   0.9407
   0.750   0.2779   0.01518   0.00650  -0.0243   0.6127   0.9477
   1.000   0.3136   0.01531   0.00652  -0.0260   0.5965   0.9567
   1.250   0.3536   0.01545   0.00654  -0.0285   0.5800   0.9634
   1.500   0.3911   0.01558   0.00658  -0.0306   0.5644   0.9711
   1.750   0.4280   0.01572   0.00662  -0.0326   0.5489   0.9790
   2.000   0.4648   0.01586   0.00668  -0.0347   0.5338   0.9866
   2.250   0.5012   0.01601   0.00674  -0.0368   0.5188   0.9943
   2.500   0.5384   0.01613   0.00678  -0.0390   0.5039   1.0000
   2.750   0.5593   0.01621   0.00683  -0.0380   0.4905   1.0000
   3.000   0.5801   0.01631   0.00689  -0.0369   0.4774   1.0000
   3.250   0.6007   0.01643   0.00697  -0.0357   0.4647   1.0000
   3.500   0.6211   0.01658   0.00705  -0.0344   0.4526   1.0000
   3.750   0.6414   0.01674   0.00717  -0.0331   0.4406   1.0000
   4.000   0.6617   0.01690   0.00732  -0.0318   0.4279   1.0000
   4.250   0.6820   0.01710   0.00749  -0.0305   0.4159   1.0000
   4.500   0.7023   0.01731   0.00768  -0.0292   0.4044   1.0000
   4.750   0.7225   0.01754   0.00787  -0.0279   0.3931   1.0000
   5.000   0.7430   0.01778   0.00812  -0.0266   0.3813   1.0000
   5.250   0.7634   0.01805   0.00837  -0.0253   0.3700   1.0000
   5.500   0.7836   0.01834   0.00863  -0.0240   0.3594   1.0000
   5.750   0.8041   0.01863   0.00895  -0.0227   0.3479   1.0000
   6.000   0.8246   0.01895   0.00929  -0.0214   0.3369   1.0000
   6.250   0.8448   0.01930   0.00962  -0.0201   0.3266   1.0000
   6.500   0.8650   0.01966   0.01000  -0.0188   0.3158   1.0000
   6.750   0.8852   0.02003   0.01041  -0.0176   0.3050   1.0000
   7.000   0.9049   0.02044   0.01081  -0.0162   0.2951   1.0000
   7.250   0.9247   0.02086   0.01128  -0.0149   0.2849   1.0000
   7.500   0.9445   0.02131   0.01178  -0.0136   0.2755   1.0000
   7.750   0.9635   0.02179   0.01224  -0.0121   0.2669   1.0000
   8.000   0.9829   0.02228   0.01283  -0.0108   0.2573   1.0000
   8.250   1.0015   0.02281   0.01337  -0.0094   0.2492   1.0000
   8.500   1.0203   0.02335   0.01400  -0.0080   0.2407   1.0000
   8.750   1.0386   0.02394   0.01460  -0.0065   0.2340   1.0000
   9.000   1.0571   0.02454   0.01532  -0.0052   0.2269   1.0000
   9.250   1.0748   0.02518   0.01596  -0.0037   0.2212   1.0000
   9.500   1.0925   0.02583   0.01677  -0.0022   0.2141   1.0000
   9.750   1.1085   0.02646   0.01741  -0.0006   0.2073   1.0000
  10.000   1.1232   0.02711   0.01820   0.0013   0.1986   1.0000
  10.250   1.1356   0.02775   0.01883   0.0033   0.1902   1.0000
  10.500   1.1472   0.02842   0.01966   0.0054   0.1807   1.0000
  10.750   1.1580   0.02917   0.02047   0.0076   0.1728   1.0000
  11.000   1.1663   0.02995   0.02133   0.0101   0.1645   1.0000
  11.250   1.1730   0.03079   0.02229   0.0128   0.1567   1.0000
  11.500   1.1762   0.03176   0.02329   0.0156   0.1490   1.0000
  11.750   1.1814   0.03282   0.02451   0.0179   0.1397   1.0000
  12.000   1.1838   0.03414   0.02593   0.0200   0.1304   1.0000
  12.250   1.1840   0.03577   0.02761   0.0219   0.1203   1.0000
  12.500   1.1841   0.03764   0.02958   0.0233   0.1084   1.0000
  12.750   1.1820   0.03992   0.03195   0.0243   0.0943   1.0000
  13.000   1.1757   0.04283   0.03489   0.0249   0.0774   1.0000
  13.250   1.1629   0.04668   0.03871   0.0248   0.0630   1.0000
  13.500   1.1480   0.05115   0.04319   0.0241   0.0543   1.0000
  13.750   1.1325   0.05604   0.04813   0.0229   0.0496   1.0000
  14.000   1.1153   0.06142   0.05360   0.0212   0.0465   1.0000
  14.250   1.0971   0.06720   0.05947   0.0192   0.0447   1.0000
  14.500   1.0799   0.07302   0.06543   0.0170   0.0433   1.0000
  14.750   1.0621   0.07913   0.07167   0.0147   0.0420   1.0000
  15.000   1.0445   0.08539   0.07805   0.0123   0.0410   1.0000
  15.250   1.0273   0.09176   0.08454   0.0097   0.0400   1.0000
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