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Falcon (falcon-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 200,000
Max Cl/Cd: 58.84 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-falcon-il-200000-n5.txt
Download as CSV file: xf-falcon-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8388   0.06841   0.06396  -0.0427   1.0000   0.0202
 -13.250  -0.8697   0.06027   0.05556  -0.0479   1.0000   0.0201
 -13.000  -0.8933   0.05439   0.04942  -0.0503   1.0000   0.0202
 -12.750  -0.9131   0.04977   0.04453  -0.0508   1.0000   0.0203
 -12.500  -0.9285   0.04611   0.04060  -0.0500   1.0000   0.0205
 -12.250  -0.9412   0.04306   0.03726  -0.0480   1.0000   0.0208
 -12.000  -0.9504   0.04060   0.03449  -0.0452   1.0000   0.0211
 -11.750  -0.9522   0.03880   0.03259  -0.0423   1.0000   0.0214
 -11.500  -0.9505   0.03746   0.03119  -0.0394   1.0000   0.0218
 -11.250  -0.9461   0.03633   0.02998  -0.0365   1.0000   0.0222
 -11.000  -0.9392   0.03504   0.02858  -0.0341   1.0000   0.0226
 -10.750  -0.9312   0.03370   0.02709  -0.0317   1.0000   0.0232
 -10.500  -0.9219   0.03227   0.02549  -0.0293   1.0000   0.0237
 -10.250  -0.9111   0.03084   0.02386  -0.0270   1.0000   0.0243
 -10.000  -0.8987   0.02948   0.02230  -0.0248   1.0000   0.0250
  -9.750  -0.8848   0.02823   0.02083  -0.0228   1.0000   0.0256
  -9.500  -0.8705   0.02708   0.01959  -0.0209   1.0000   0.0264
  -9.250  -0.8549   0.02623   0.01873  -0.0191   1.0000   0.0272
  -9.000  -0.8386   0.02546   0.01790  -0.0174   1.0000   0.0281
  -8.750  -0.8219   0.02462   0.01698  -0.0156   1.0000   0.0292
  -8.500  -0.8050   0.02376   0.01600  -0.0138   1.0000   0.0302
  -8.250  -0.7879   0.02293   0.01505  -0.0119   1.0000   0.0312
  -8.000  -0.7724   0.02206   0.01415  -0.0099   1.0000   0.0322
  -7.750  -0.7562   0.02144   0.01353  -0.0080   1.0000   0.0335
  -7.500  -0.7400   0.02089   0.01294  -0.0060   1.0000   0.0350
  -7.250  -0.7243   0.02033   0.01232  -0.0038   1.0000   0.0367
  -6.750  -0.6716   0.01888   0.01080  -0.0041   0.9922   0.0407
  -6.500  -0.6419   0.01825   0.01013  -0.0048   0.9813   0.0438
  -6.250  -0.6100   0.01759   0.00945  -0.0059   0.9734   0.0475
  -6.000  -0.5748   0.01700   0.00883  -0.0077   0.9675   0.0523
  -5.750  -0.5401   0.01641   0.00824  -0.0093   0.9608   0.0577
  -5.500  -0.5011   0.01590   0.00771  -0.0119   0.9555   0.0658
  -5.250  -0.4644   0.01542   0.00724  -0.0139   0.9477   0.0753
  -5.000  -0.4250   0.01495   0.00680  -0.0166   0.9405   0.0868
  -4.750  -0.3899   0.01456   0.00642  -0.0183   0.9294   0.0984
  -4.500  -0.3561   0.01420   0.00606  -0.0196   0.9169   0.1106
  -4.250  -0.3240   0.01387   0.00573  -0.0206   0.9027   0.1236
  -4.000  -0.2939   0.01356   0.00541  -0.0211   0.8868   0.1377
  -3.750  -0.2658   0.01325   0.00511  -0.0211   0.8693   0.1540
  -3.500  -0.2392   0.01290   0.00479  -0.0208   0.8505   0.1751
  -3.000  -0.1979   0.01158   0.00413  -0.0182   0.8092   0.3484
  -2.750  -0.1784   0.01109   0.00394  -0.0164   0.7875   0.4436
  -2.500  -0.1574   0.01077   0.00378  -0.0148   0.7660   0.5108
  -2.250  -0.1356   0.01054   0.00366  -0.0132   0.7445   0.5640
  -2.000  -0.1134   0.01037   0.00357  -0.0117   0.7234   0.6122
  -1.750  -0.0905   0.01026   0.00352  -0.0103   0.7036   0.6562
  -1.500  -0.0667   0.01020   0.00348  -0.0090   0.6847   0.6979
  -1.250  -0.0420   0.01019   0.00346  -0.0080   0.6665   0.7326
  -1.000  -0.0166   0.01020   0.00346  -0.0071   0.6494   0.7643
  -0.750   0.0100   0.01024   0.00347  -0.0065   0.6330   0.7910
  -0.500   0.0370   0.01030   0.00348  -0.0060   0.6175   0.8162
   0.000   0.0949   0.01047   0.00357  -0.0058   0.5878   0.8635
   0.250   0.1272   0.01058   0.00362  -0.0064   0.5733   0.8814
   0.500   0.1591   0.01069   0.00365  -0.0072   0.5592   0.8935
   0.750   0.1933   0.01081   0.00369  -0.0084   0.5454   0.9031
   1.000   0.2249   0.01092   0.00372  -0.0092   0.5322   0.9137
   1.250   0.2607   0.01107   0.00378  -0.0108   0.5186   0.9220
   1.500   0.2948   0.01121   0.00383  -0.0121   0.5050   0.9306
   1.750   0.3310   0.01135   0.00392  -0.0139   0.4911   0.9383
   2.000   0.3678   0.01151   0.00400  -0.0159   0.4772   0.9452
   2.250   0.4057   0.01168   0.00411  -0.0180   0.4630   0.9513
   2.500   0.4410   0.01185   0.00422  -0.0197   0.4490   0.9577
   2.750   0.4780   0.01204   0.00434  -0.0217   0.4350   0.9622
   3.000   0.5113   0.01223   0.00446  -0.0229   0.4217   0.9684
   3.500   0.5811   0.01262   0.00474  -0.0262   0.3947   0.9783
   3.750   0.6157   0.01281   0.00491  -0.0279   0.3820   0.9837
   4.000   0.6487   0.01303   0.00508  -0.0292   0.3698   0.9905
   4.250   0.6829   0.01326   0.00527  -0.0308   0.3578   0.9961
   4.500   0.7190   0.01347   0.00545  -0.0328   0.3451   0.9999
   4.750   0.7400   0.01361   0.00558  -0.0317   0.3348   1.0000
   5.000   0.7601   0.01378   0.00573  -0.0303   0.3254   1.0000
   5.250   0.7803   0.01397   0.00590  -0.0290   0.3152   1.0000
   5.500   0.8008   0.01416   0.00609  -0.0277   0.3049   1.0000
   5.750   0.8211   0.01439   0.00629  -0.0264   0.2952   1.0000
   6.000   0.8418   0.01462   0.00652  -0.0251   0.2855   1.0000
   6.250   0.8627   0.01487   0.00678  -0.0239   0.2762   1.0000
   6.750   0.9042   0.01544   0.00734  -0.0214   0.2565   1.0000
   7.000   0.9248   0.01575   0.00765  -0.0202   0.2470   1.0000
   7.250   0.9452   0.01609   0.00799  -0.0189   0.2378   1.0000
   7.500   0.9661   0.01642   0.00835  -0.0178   0.2295   1.0000
   7.750   0.9859   0.01682   0.00873  -0.0164   0.2216   1.0000
   8.000   1.0067   0.01717   0.00914  -0.0152   0.2138   1.0000
   8.250   1.0256   0.01762   0.00957  -0.0138   0.2059   1.0000
   8.500   1.0456   0.01800   0.01000  -0.0125   0.1963   1.0000
   8.750   1.0643   0.01846   0.01045  -0.0111   0.1866   1.0000
   9.000   1.0816   0.01898   0.01094  -0.0095   0.1768   1.0000
   9.250   1.1007   0.01941   0.01143  -0.0082   0.1678   1.0000
   9.500   1.1180   0.01993   0.01196  -0.0066   0.1597   1.0000
   9.750   1.1350   0.02046   0.01250  -0.0051   0.1509   1.0000
  10.000   1.1520   0.02098   0.01307  -0.0035   0.1433   1.0000
  10.250   1.1664   0.02162   0.01371  -0.0016   0.1345   1.0000
  10.500   1.1824   0.02217   0.01432   0.0001   0.1249   1.0000
  10.750   1.1962   0.02282   0.01500   0.0020   0.1159   1.0000
  11.000   1.2070   0.02358   0.01575   0.0044   0.1030   1.0000
  11.250   1.2124   0.02450   0.01662   0.0075   0.0858   1.0000
  11.750   1.1976   0.02815   0.01989   0.0155   0.0364   1.0000
  12.000   1.1945   0.03004   0.02179   0.0182   0.0304   1.0000
  12.250   1.1953   0.03182   0.02365   0.0201   0.0275   1.0000
  12.500   1.1943   0.03390   0.02583   0.0217   0.0256   1.0000
  12.750   1.1947   0.03605   0.02809   0.0227   0.0243   1.0000
  13.000   1.1948   0.03840   0.03059   0.0234   0.0233   1.0000
  13.250   1.1927   0.04115   0.03347   0.0237   0.0224   1.0000
  13.500   1.1887   0.04431   0.03676   0.0235   0.0217   1.0000
  13.750   1.1826   0.04790   0.04049   0.0229   0.0212   1.0000
  14.000   1.1733   0.05205   0.04478   0.0220   0.0208   1.0000
  14.250   1.1625   0.05659   0.04946   0.0207   0.0204   1.0000
  14.500   1.1541   0.06091   0.05393   0.0194   0.0201   1.0000
  14.750   1.1438   0.06562   0.05878   0.0178   0.0198   1.0000
  15.000   1.1325   0.07055   0.06386   0.0161   0.0196   1.0000
  15.250   1.1203   0.07580   0.06925   0.0142   0.0193   1.0000
  15.500   1.1079   0.08121   0.07478   0.0121   0.0191   1.0000
  15.750   1.0953   0.08677   0.08047   0.0100   0.0188   1.0000
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