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FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FAUVEL 14% AIRFOIL (fauvel-il)
Reynolds number: 50,000
Max Cl/Cd: 9.94 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fauvel-il-50000.txt
Download as CSV file: xf-fauvel-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FAUVEL 14% AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4551   0.11979   0.11388   0.0257   1.0000   0.2889
  -9.500  -0.4345   0.11489   0.10906   0.0254   1.0000   0.2976
  -9.250  -0.4678   0.11466   0.10901   0.0229   1.0000   0.3099
  -9.000  -0.4174   0.10796   0.10231   0.0235   1.0000   0.3206
  -8.750  -0.4181   0.10473   0.09920   0.0222   1.0000   0.3329
  -8.500  -0.4358   0.10316   0.09779   0.0207   1.0000   0.3484
  -8.250  -0.3997   0.09824   0.09291   0.0203   1.0000   0.3639
  -8.000  -0.3819   0.09444   0.08922   0.0194   1.0000   0.3808
  -7.750  -0.3922   0.09250   0.08742   0.0187   1.0000   0.4042
  -7.500  -0.3746   0.08874   0.08379   0.0177   1.0000   0.4243
  -7.250  -0.3469   0.08478   0.07991   0.0163   1.0000   0.4442
  -7.000  -0.3213   0.08125   0.07647   0.0145   1.0000   0.4647
  -6.750  -0.4971   0.06086   0.05531  -0.0182   0.9461   0.1944
  -6.500  -0.4993   0.05346   0.04683  -0.0214   0.9243   0.1678
  -6.250  -0.4710   0.04958   0.04265  -0.0231   0.9025   0.1636
  -6.000  -0.4526   0.04623   0.03890  -0.0230   0.8831   0.1590
  -5.750  -0.4399   0.04313   0.03511  -0.0214   0.8663   0.1539
  -5.500  -0.4247   0.04101   0.03225  -0.0194   0.8506   0.1515
  -5.250  -0.4033   0.03916   0.03024  -0.0183   0.8352   0.1534
  -5.000  -0.3817   0.03777   0.02867  -0.0170   0.8202   0.1564
  -4.750  -0.3589   0.03637   0.02700  -0.0161   0.8055   0.1586
  -4.500  -0.3337   0.03505   0.02538  -0.0153   0.7920   0.1610
  -4.250  -0.3071   0.03395   0.02393  -0.0145   0.7793   0.1648
  -4.000  -0.2789   0.03299   0.02293  -0.0140   0.7667   0.1723
  -3.750  -0.2467   0.03225   0.02203  -0.0145   0.7537   0.1825
  -3.500  -0.2091   0.03144   0.02132  -0.0156   0.7415   0.1970
  -3.250  -0.1742   0.03075   0.02078  -0.0158   0.7303   0.2242
  -3.000   0.1188   0.02992   0.02219  -0.0438   0.6994   1.0000
  -2.750   0.1375   0.03020   0.02221  -0.0431   0.6905   1.0000
  -2.500   0.1596   0.03054   0.02237  -0.0437   0.6803   1.0000
  -2.250   0.1785   0.03097   0.02259  -0.0429   0.6723   1.0000
  -2.000   0.2010   0.03145   0.02294  -0.0435   0.6626   1.0000
  -1.750   0.2192   0.03197   0.02327  -0.0424   0.6552   1.0000
  -1.500   0.2430   0.03265   0.02388  -0.0436   0.6462   1.0000
  -1.250   0.2612   0.03323   0.02431  -0.0425   0.6395   1.0000
  -1.000   0.2843   0.03413   0.02516  -0.0438   0.6311   1.0000
  -0.750   0.3031   0.03482   0.02574  -0.0431   0.6240   1.0000
  -0.500   0.3236   0.03584   0.02670  -0.0436   0.6174   1.0000
  -0.250   0.3438   0.03691   0.02774  -0.0443   0.6105   1.0000
   0.000   0.3606   0.03769   0.02839  -0.0428   0.6050   1.0000
   0.250   0.3795   0.03925   0.02999  -0.0446   0.5979   1.0000
   0.500   0.3961   0.04051   0.03121  -0.0446   0.5923   1.0000
   0.750   0.4120   0.04145   0.03205  -0.0430   0.5879   1.0000
   1.000   0.4236   0.04364   0.03431  -0.0449   0.5825   1.0000
   1.250   0.4336   0.04540   0.03606  -0.0449   0.5775   1.0000
   1.500   0.4450   0.04687   0.03749  -0.0439   0.5736   1.0000
   1.750   0.4561   0.04844   0.03900  -0.0426   0.5706   1.0000
   2.000   0.4512   0.05118   0.04178  -0.0428   0.5687   1.0000
   2.250   0.4435   0.05371   0.04430  -0.0417   0.5680   1.0000
   2.500   0.4375   0.05608   0.04665  -0.0402   0.5691   1.0000
   3.250   0.2145   0.06552   0.05604  -0.0262   0.7474   1.0000
   3.500   0.2297   0.06713   0.05757  -0.0250   0.7295   1.0000
   3.750   0.2329   0.06792   0.05827  -0.0223   0.7129   1.0000
   4.000   0.2369   0.06901   0.05927  -0.0200   0.6973   1.0000
   4.250   0.2447   0.07052   0.06071  -0.0183   0.6835   1.0000
   4.500   0.2788   0.07398   0.06412  -0.0199   0.6736   1.0000
   4.750   0.2762   0.07445   0.06452  -0.0170   0.6593   1.0000
   5.000   0.2778   0.07580   0.06580  -0.0150   0.6480   1.0000
   5.250   0.3149   0.07963   0.06962  -0.0167   0.6387   1.0000
   5.500   0.3043   0.07970   0.06962  -0.0134   0.6254   1.0000
   5.750   0.3113   0.08166   0.07153  -0.0123   0.6168   1.0000
   6.000   0.3338   0.08433   0.07418  -0.0125   0.6059   1.0000
   6.250   0.3291   0.08527   0.07508  -0.0104   0.5944   1.0000
   6.500   0.3555   0.08888   0.07867  -0.0111   0.5867   1.0000
   6.750   0.3554   0.08981   0.07958  -0.0094   0.5741   1.0000
   7.000   0.3568   0.09152   0.08126  -0.0082   0.5644   1.0000
   7.250   0.3914   0.09578   0.08554  -0.0093   0.5548   1.0000
   7.500   0.3792   0.09597   0.08569  -0.0071   0.5425   1.0000
   7.750   0.3878   0.09848   0.08820  -0.0067   0.5339   1.0000
   8.000   0.4107   0.10165   0.09138  -0.0069   0.5223   1.0000
   8.250   0.4025   0.10267   0.09238  -0.0056   0.5115   1.0000
   8.500   0.4287   0.10684   0.09657  -0.0062   0.5032   1.0000
   8.750   0.4264   0.10782   0.09755  -0.0051   0.4906   1.0000
   9.000   0.4307   0.11039   0.10012  -0.0049   0.4828   1.0000
   9.250   0.4505   0.11347   0.10323  -0.0049   0.4715   1.0000
   9.500   0.4440   0.11499   0.10474  -0.0043   0.4618   1.0000
   9.750   0.4740   0.11947   0.10926  -0.0048   0.4530   1.0000
  10.000   0.4593   0.12020   0.10997  -0.0043   0.4442   1.0000
  10.250   0.4895   0.12477   0.11460  -0.0047   0.4354   1.0000
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