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Falcon (falcon-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 500,000
Max Cl/Cd: 81.78 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-falcon-il-500000.txt
Download as CSV file: xf-falcon-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.9315   0.06645   0.06322  -0.0431   1.0000   0.0179
 -14.250  -0.9597   0.05868   0.05521  -0.0479   1.0000   0.0178
 -14.000  -0.9818   0.05276   0.04908  -0.0506   1.0000   0.0178
 -13.750  -0.9948   0.04868   0.04483  -0.0515   1.0000   0.0179
 -13.500  -1.0052   0.04527   0.04126  -0.0514   1.0000   0.0180
 -13.250  -1.0107   0.04272   0.03859  -0.0506   1.0000   0.0182
 -13.000  -1.0165   0.04034   0.03606  -0.0491   1.0000   0.0184
 -12.750  -1.0207   0.03830   0.03389  -0.0470   1.0000   0.0186
 -12.500  -1.0239   0.03649   0.03193  -0.0443   1.0000   0.0188
 -12.250  -1.0245   0.03503   0.03036  -0.0412   1.0000   0.0191
 -12.000  -1.0252   0.03370   0.02889  -0.0376   1.0000   0.0194
 -11.750  -1.0232   0.03246   0.02751  -0.0342   1.0000   0.0198
 -11.500  -1.0168   0.03112   0.02601  -0.0314   1.0000   0.0202
 -11.250  -1.0083   0.02990   0.02461  -0.0288   1.0000   0.0206
 -11.000  -0.9976   0.02883   0.02337  -0.0263   1.0000   0.0210
 -10.750  -0.9884   0.02710   0.02142  -0.0238   1.0000   0.0213
 -10.500  -0.9771   0.02529   0.01952  -0.0216   1.0000   0.0219
 -10.250  -0.9617   0.02435   0.01854  -0.0198   1.0000   0.0224
 -10.000  -0.9452   0.02357   0.01771  -0.0181   1.0000   0.0230
  -9.750  -0.9283   0.02278   0.01685  -0.0163   1.0000   0.0236
  -9.500  -0.9109   0.02201   0.01599  -0.0146   1.0000   0.0243
  -9.250  -0.8931   0.02126   0.01514  -0.0129   1.0000   0.0249
  -9.000  -0.8744   0.02073   0.01451  -0.0112   1.0000   0.0256
  -8.750  -0.8593   0.01954   0.01325  -0.0091   1.0000   0.0265
  -8.500  -0.8437   0.01877   0.01247  -0.0070   1.0000   0.0274
  -8.250  -0.8279   0.01826   0.01195  -0.0049   1.0000   0.0282
  -8.000  -0.8138   0.01779   0.01145  -0.0023   1.0000   0.0291
  -7.750  -0.8004   0.01735   0.01095   0.0003   1.0000   0.0300
  -7.500  -0.7753   0.01686   0.01040   0.0006   0.9990   0.0310
  -7.250  -0.7427   0.01587   0.00937  -0.0008   0.9963   0.0327
  -7.000  -0.7086   0.01529   0.00881  -0.0024   0.9925   0.0347
  -6.750  -0.6752   0.01478   0.00825  -0.0038   0.9864   0.0368
  -6.500  -0.6433   0.01410   0.00753  -0.0048   0.9801   0.0390
  -6.250  -0.6102   0.01350   0.00696  -0.0061   0.9746   0.0423
  -6.000  -0.5741   0.01311   0.00652  -0.0078   0.9699   0.0457
  -5.750  -0.5374   0.01242   0.00588  -0.0099   0.9662   0.0516
  -5.500  -0.4994   0.01192   0.00540  -0.0122   0.9607   0.0589
  -5.250  -0.4556   0.01145   0.00497  -0.0158   0.9567   0.0697
  -5.000  -0.4134   0.01105   0.00463  -0.0191   0.9500   0.0829
  -4.750  -0.3705   0.01072   0.00432  -0.0225   0.9418   0.0966
  -4.500  -0.3362   0.01049   0.00410  -0.0239   0.9290   0.1089
  -4.250  -0.3064   0.01032   0.00392  -0.0243   0.9144   0.1204
  -4.000  -0.2798   0.01012   0.00372  -0.0239   0.8988   0.1331
  -3.750  -0.2545   0.00990   0.00351  -0.0233   0.8820   0.1471
  -3.500  -0.2297   0.00967   0.00330  -0.0225   0.8639   0.1646
  -3.250  -0.2068   0.00936   0.00305  -0.0214   0.8435   0.1937
  -3.000  -0.1911   0.00853   0.00272  -0.0191   0.8210   0.3291
  -2.750  -0.1736   0.00802   0.00254  -0.0169   0.7981   0.4404
  -2.500  -0.1543   0.00771   0.00241  -0.0150   0.7741   0.5117
  -2.250  -0.1343   0.00751   0.00231  -0.0131   0.7506   0.5700
  -2.000  -0.1136   0.00735   0.00223  -0.0114   0.7277   0.6183
  -1.750  -0.0931   0.00723   0.00219  -0.0095   0.7060   0.6661
  -1.500  -0.0715   0.00716   0.00217  -0.0079   0.6859   0.7063
  -1.250  -0.0488   0.00715   0.00216  -0.0065   0.6674   0.7402
  -1.000  -0.0255   0.00715   0.00216  -0.0053   0.6497   0.7704
  -0.750  -0.0013   0.00717   0.00216  -0.0042   0.6334   0.7951
  -0.500   0.0234   0.00720   0.00218  -0.0033   0.6180   0.8170
  -0.250   0.0489   0.00724   0.00220  -0.0025   0.6030   0.8371
   0.000   0.0753   0.00728   0.00222  -0.0020   0.5887   0.8544
   0.250   0.1022   0.00733   0.00225  -0.0015   0.5750   0.8720
   0.500   0.1300   0.00739   0.00229  -0.0013   0.5614   0.8887
   0.750   0.1591   0.00747   0.00233  -0.0014   0.5481   0.9050
   1.000   0.1904   0.00756   0.00238  -0.0019   0.5346   0.9214
   1.500   0.2595   0.00776   0.00246  -0.0047   0.5066   0.9435
   1.750   0.3014   0.00790   0.00254  -0.0079   0.4914   0.9483
   2.000   0.3384   0.00803   0.00261  -0.0099   0.4771   0.9551
   2.250   0.3804   0.00820   0.00270  -0.0131   0.4624   0.9580
   2.500   0.4205   0.00838   0.00282  -0.0158   0.4480   0.9610
   2.750   0.4577   0.00857   0.00295  -0.0178   0.4344   0.9650
   3.000   0.4938   0.00878   0.00309  -0.0196   0.4214   0.9693
   3.250   0.5319   0.00901   0.00325  -0.0219   0.4078   0.9723
   3.500   0.5683   0.00920   0.00340  -0.0238   0.3950   0.9766
   3.750   0.6045   0.00939   0.00355  -0.0257   0.3829   0.9804
   4.000   0.6403   0.00959   0.00370  -0.0276   0.3708   0.9844
   4.250   0.6749   0.00980   0.00386  -0.0292   0.3585   0.9889
   4.500   0.7106   0.01000   0.00402  -0.0311   0.3466   0.9929
   4.750   0.7469   0.01017   0.00417  -0.0331   0.3352   0.9960
   5.000   0.7842   0.01034   0.00430  -0.0353   0.3235   0.9985
   5.250   0.8171   0.01052   0.00444  -0.0367   0.3115   1.0000
   5.500   0.8378   0.01062   0.00453  -0.0355   0.3012   1.0000
   5.750   0.8583   0.01075   0.00464  -0.0342   0.2916   1.0000
   6.000   0.8781   0.01093   0.00479  -0.0327   0.2817   1.0000
   6.250   0.8986   0.01107   0.00493  -0.0314   0.2718   1.0000
   6.500   0.9188   0.01127   0.00511  -0.0300   0.2620   1.0000
   7.000   0.9601   0.01174   0.00552  -0.0274   0.2401   1.0000
   7.250   0.9811   0.01200   0.00574  -0.0262   0.2274   1.0000
   7.500   1.0021   0.01229   0.00599  -0.0250   0.2150   1.0000
   7.750   1.0230   0.01262   0.00627  -0.0238   0.2038   1.0000
   8.000   1.0439   0.01296   0.00657  -0.0226   0.1930   1.0000
   8.250   1.0657   0.01325   0.00687  -0.0216   0.1841   1.0000
   8.500   1.0863   0.01363   0.00722  -0.0204   0.1759   1.0000
   8.750   1.1080   0.01394   0.00754  -0.0194   0.1676   1.0000
   9.000   1.1288   0.01431   0.00790  -0.0182   0.1592   1.0000
   9.250   1.1494   0.01469   0.00827  -0.0171   0.1510   1.0000
   9.500   1.1705   0.01505   0.00864  -0.0160   0.1436   1.0000
   9.750   1.1896   0.01552   0.00908  -0.0147   0.1344   1.0000
  10.000   1.2102   0.01589   0.00946  -0.0136   0.1248   1.0000
  10.250   1.2279   0.01645   0.00995  -0.0121   0.1098   1.0000
  10.500   1.2361   0.01763   0.01083  -0.0092   0.0687   1.0000
  10.750   1.2306   0.01961   0.01249  -0.0044   0.0304   1.0000
  11.000   1.2385   0.02066   0.01357  -0.0014   0.0257   1.0000
  11.250   1.2462   0.02145   0.01444   0.0017   0.0237   1.0000
  11.500   1.2509   0.02233   0.01537   0.0052   0.0223   1.0000
  11.750   1.2528   0.02345   0.01657   0.0087   0.0211   1.0000
  12.000   1.2545   0.02474   0.01795   0.0117   0.0202   1.0000
  12.250   1.2602   0.02592   0.01922   0.0139   0.0196   1.0000
  12.500   1.2644   0.02732   0.02071   0.0159   0.0190   1.0000
  12.750   1.2668   0.02899   0.02247   0.0177   0.0184   1.0000
  13.000   1.2681   0.03092   0.02450   0.0191   0.0180   1.0000
  13.250   1.2670   0.03325   0.02694   0.0201   0.0176   1.0000
  13.500   1.2632   0.03609   0.02988   0.0206   0.0172   1.0000
  13.750   1.2563   0.03953   0.03343   0.0205   0.0169   1.0000
  14.000   1.2451   0.04371   0.03773   0.0200   0.0166   1.0000
  14.250   1.2325   0.04824   0.04237   0.0191   0.0164   1.0000
  14.500   1.2297   0.05172   0.04596   0.0183   0.0163   1.0000
  14.750   1.2248   0.05551   0.04986   0.0174   0.0161   1.0000
  15.000   1.2182   0.05955   0.05401   0.0163   0.0159   1.0000
  15.250   1.2110   0.06373   0.05830   0.0151   0.0157   1.0000
  15.500   1.2034   0.06808   0.06275   0.0138   0.0155   1.0000
  15.750   1.1950   0.07256   0.06733   0.0125   0.0154   1.0000
  16.000   1.1875   0.07704   0.07190   0.0110   0.0152   1.0000
  16.250   1.1802   0.08155   0.07650   0.0095   0.0150   1.0000
  16.500   1.1733   0.08601   0.08104   0.0081   0.0148   1.0000
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