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Falcon (falcon-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 200,000
Max Cl/Cd: 58.13 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-falcon-il-200000.txt
Download as CSV file: xf-falcon-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6743   0.07406   0.07012  -0.0450   1.0000   0.0454
 -11.000  -0.6884   0.06910   0.06514  -0.0463   1.0000   0.0449
 -10.750  -0.7116   0.06427   0.06021  -0.0468   1.0000   0.0444
 -10.500  -0.7364   0.06018   0.05600  -0.0450   1.0000   0.0440
 -10.250  -0.7613   0.05662   0.05228  -0.0411   1.0000   0.0435
 -10.000  -0.7826   0.05246   0.04789  -0.0373   1.0000   0.0432
  -9.750  -0.7992   0.04823   0.04335  -0.0332   1.0000   0.0429
  -9.500  -0.8106   0.04413   0.03889  -0.0292   1.0000   0.0428
  -9.250  -0.8164   0.04029   0.03466  -0.0252   1.0000   0.0427
  -9.000  -0.8164   0.03693   0.03090  -0.0215   1.0000   0.0429
  -8.750  -0.8109   0.03413   0.02773  -0.0183   1.0000   0.0434
  -8.500  -0.8019   0.03180   0.02504  -0.0153   1.0000   0.0442
  -8.250  -0.7904   0.03026   0.02313  -0.0125   1.0000   0.0454
  -8.000  -0.7773   0.02796   0.02061  -0.0103   1.0000   0.0468
  -7.750  -0.7607   0.02672   0.01937  -0.0086   1.0000   0.0483
  -7.500  -0.7446   0.02564   0.01819  -0.0065   1.0000   0.0497
  -7.250  -0.7284   0.02456   0.01699  -0.0044   1.0000   0.0514
  -7.000  -0.7125   0.02366   0.01592  -0.0022   1.0000   0.0534
  -6.750  -0.6963   0.02263   0.01473   0.0000   1.0000   0.0555
  -6.500  -0.6798   0.02161   0.01376   0.0018   1.0000   0.0581
  -6.250  -0.6634   0.02097   0.01311   0.0038   1.0000   0.0607
  -6.000  -0.6467   0.02035   0.01240   0.0058   1.0000   0.0638
  -5.750  -0.6305   0.01951   0.01154   0.0077   1.0000   0.0675
  -5.500  -0.6136   0.01910   0.01117   0.0094   0.9999   0.0720
  -5.250  -0.5715   0.01819   0.01025   0.0063   0.9952   0.0801
  -5.000  -0.5294   0.01759   0.00962   0.0031   0.9886   0.0909
  -4.750  -0.4889   0.01691   0.00898   0.0003   0.9811   0.1046
  -4.500  -0.4489   0.01613   0.00831  -0.0025   0.9738   0.1213
  -4.250  -0.4062   0.01541   0.00768  -0.0058   0.9678   0.1404
  -4.000  -0.3663   0.01474   0.00709  -0.0084   0.9598   0.1613
  -3.750  -0.3220   0.01390   0.00640  -0.0120   0.9549   0.1894
  -3.500  -0.2861   0.01283   0.00574  -0.0141   0.9452   0.2521
  -3.250  -0.2625   0.01132   0.00539  -0.0136   0.9330   0.5027
  -3.000  -0.2328   0.01076   0.00525  -0.0135   0.9194   0.6088
  -2.750  -0.2033   0.01047   0.00519  -0.0132   0.9039   0.6771
  -2.500  -0.1751   0.01032   0.00516  -0.0124   0.8866   0.7287
  -2.250  -0.1473   0.01024   0.00510  -0.0116   0.8683   0.7666
  -2.000  -0.1193   0.01020   0.00504  -0.0108   0.8496   0.7985
  -1.750  -0.0893   0.01020   0.00499  -0.0103   0.8307   0.8250
  -1.500  -0.0614   0.01024   0.00497  -0.0096   0.8091   0.8491
  -1.250  -0.0298   0.01033   0.00497  -0.0096   0.7880   0.8690
  -1.000   0.0031   0.01047   0.00498  -0.0099   0.7675   0.8876
  -0.750   0.0381   0.01066   0.00503  -0.0107   0.7467   0.9040
  -0.500   0.0764   0.01089   0.00513  -0.0122   0.7255   0.9184
  -0.250   0.1194   0.01120   0.00528  -0.0147   0.7050   0.9316
   0.000   0.1623   0.01150   0.00541  -0.0173   0.6855   0.9429
   0.250   0.2090   0.01176   0.00550  -0.0211   0.6655   0.9472
   0.500   0.2444   0.01193   0.00554  -0.0225   0.6472   0.9561
   0.750   0.2891   0.01212   0.00560  -0.0260   0.6284   0.9603
   1.000   0.3260   0.01229   0.00565  -0.0279   0.6113   0.9683
   1.250   0.3693   0.01245   0.00569  -0.0312   0.5934   0.9732
   1.500   0.4087   0.01259   0.00573  -0.0337   0.5765   0.9800
   1.750   0.4489   0.01274   0.00577  -0.0365   0.5598   0.9867
   2.000   0.4909   0.01282   0.00577  -0.0397   0.5428   0.9927
   2.250   0.5332   0.01288   0.00573  -0.0430   0.5261   0.9981
   2.500   0.5633   0.01291   0.00569  -0.0439   0.5111   1.0000
   2.750   0.5845   0.01295   0.00568  -0.0429   0.4979   1.0000
   3.000   0.6057   0.01302   0.00567  -0.0419   0.4853   1.0000
   3.250   0.6268   0.01309   0.00567  -0.0408   0.4729   1.0000
   3.500   0.6479   0.01315   0.00572  -0.0398   0.4598   1.0000
   3.750   0.6690   0.01324   0.00578  -0.0387   0.4475   1.0000
   4.000   0.6900   0.01336   0.00585  -0.0376   0.4359   1.0000
   4.250   0.7109   0.01351   0.00592  -0.0364   0.4245   1.0000
   4.500   0.7313   0.01362   0.00605  -0.0351   0.4122   1.0000
   4.750   0.7517   0.01378   0.00620  -0.0338   0.4009   1.0000
   5.000   0.7720   0.01398   0.00634  -0.0324   0.3900   1.0000
   5.250   0.7921   0.01417   0.00651  -0.0310   0.3784   1.0000
   5.500   0.8123   0.01436   0.00672  -0.0297   0.3666   1.0000
   5.750   0.8326   0.01461   0.00693  -0.0283   0.3555   1.0000
   6.000   0.8529   0.01490   0.00715  -0.0270   0.3449   1.0000
   6.250   0.8734   0.01513   0.00743  -0.0256   0.3330   1.0000
   6.500   0.8939   0.01542   0.00772  -0.0243   0.3214   1.0000
   6.750   0.9142   0.01576   0.00801  -0.0230   0.3102   1.0000
   7.000   0.9345   0.01610   0.00832  -0.0216   0.2989   1.0000
   7.250   0.9551   0.01643   0.00871  -0.0203   0.2875   1.0000
   7.500   0.9755   0.01685   0.00911  -0.0191   0.2773   1.0000
   7.750   0.9957   0.01730   0.00950  -0.0178   0.2675   1.0000
   8.000   1.0159   0.01769   0.00998  -0.0165   0.2573   1.0000
   8.250   1.0357   0.01818   0.01043  -0.0152   0.2480   1.0000
   8.500   1.0550   0.01858   0.01083  -0.0137   0.2382   1.0000
   8.750   1.0740   0.01898   0.01130  -0.0123   0.2283   1.0000
   9.000   1.0924   0.01946   0.01175  -0.0108   0.2193   1.0000
   9.250   1.1109   0.01984   0.01220  -0.0093   0.2103   1.0000
   9.500   1.1288   0.02033   0.01272  -0.0078   0.2021   1.0000
   9.750   1.1460   0.02077   0.01318  -0.0062   0.1939   1.0000
  10.000   1.1633   0.02125   0.01374  -0.0046   0.1861   1.0000
  10.250   1.1787   0.02176   0.01425  -0.0028   0.1781   1.0000
  10.500   1.1952   0.02221   0.01484  -0.0012   0.1705   1.0000
  10.750   1.2084   0.02280   0.01541   0.0009   0.1629   1.0000
  11.000   1.2233   0.02319   0.01598   0.0028   0.1534   1.0000
  11.250   1.2347   0.02372   0.01657   0.0051   0.1412   1.0000
  11.500   1.2418   0.02435   0.01723   0.0081   0.1248   1.0000
  11.750   1.2426   0.02549   0.01823   0.0115   0.0947   1.0000
  12.000   1.2303   0.02769   0.02012   0.0158   0.0580   1.0000
  12.250   1.2209   0.03001   0.02235   0.0190   0.0472   1.0000
  12.500   1.2156   0.03230   0.02469   0.0213   0.0428   1.0000
  12.750   1.2106   0.03480   0.02728   0.0228   0.0401   1.0000
  13.000   1.2028   0.03781   0.03039   0.0238   0.0383   1.0000
  13.250   1.1943   0.04120   0.03390   0.0241   0.0370   1.0000
  13.500   1.1893   0.04448   0.03733   0.0240   0.0359   1.0000
  13.750   1.1829   0.04810   0.04108   0.0236   0.0349   1.0000
  14.000   1.1748   0.05206   0.04516   0.0228   0.0340   1.0000
  14.250   1.1657   0.05625   0.04947   0.0218   0.0332   1.0000
  14.500   1.1559   0.06058   0.05390   0.0207   0.0326   1.0000
  14.750   1.1454   0.06503   0.05842   0.0196   0.0320   1.0000
  15.000   1.1349   0.06943   0.06286   0.0186   0.0314   1.0000
  15.250   1.1286   0.07316   0.06661   0.0181   0.0307   1.0000
  15.500   1.1266   0.07666   0.07021   0.0173   0.0303   1.0000
  15.750   1.1253   0.08000   0.07365   0.0166   0.0298   1.0000
  16.000   1.1251   0.08322   0.07694   0.0161   0.0293   1.0000
  16.250   1.1255   0.08637   0.08018   0.0155   0.0288   1.0000
  16.500   1.1271   0.08933   0.08321   0.0151   0.0283   1.0000
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