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AH 93-W-300 (ah93w300-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AH 93-W-300 (ah93w300-il)
Reynolds number: 100,000
Max Cl/Cd: 17.86 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah93w300-il-100000.txt
Download as CSV file: xf-ah93w300-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 93-W-300                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0311   0.12277   0.11649  -0.0567   0.9525   0.3742
 -10.000   0.0341   0.11857   0.11228  -0.0615   0.9427   0.3779
  -9.750   0.0687   0.11591   0.10958  -0.0651   0.9323   0.3857
  -9.500   0.1559   0.11220   0.10600  -0.0766   0.8695   0.3912
  -9.250   0.1718   0.10880   0.10251  -0.0769   0.8590   0.3934
  -9.000   0.2035   0.10661   0.10032  -0.0770   0.8424   0.3964
  -8.750   0.2231   0.10496   0.09860  -0.0766   0.8307   0.4019
  -8.500   0.1798   0.10445   0.09800  -0.0748   0.8250   0.4116
  -8.250   0.2201   0.10142   0.09497  -0.0755   0.8098   0.4137
  -8.000   0.1191   0.10321   0.09645  -0.0688   0.8388   0.4305
  -7.750   0.1459   0.09979   0.09292  -0.0690   0.8272   0.4323
  -7.500   0.1836   0.09744   0.09058  -0.0695   0.8120   0.4350
  -7.250   0.2091   0.09587   0.08894  -0.0692   0.7999   0.4395
  -7.000   0.1411   0.09736   0.09032  -0.0660   0.7940   0.4517
  -6.750   0.1908   0.09363   0.08661  -0.0674   0.7798   0.4533
  -6.500   0.2299   0.09127   0.08417  -0.0677   0.7683   0.4560
  -6.250   0.2570   0.08990   0.08276  -0.0678   0.7575   0.4607
  -6.000   0.1961   0.09151   0.08435  -0.0645   0.7506   0.4734
  -5.750   0.2290   0.08810   0.08088  -0.0652   0.7401   0.4749
  -5.500   0.2745   0.08566   0.07832  -0.0660   0.7305   0.4776
  -5.250   0.3047   0.08422   0.07694  -0.0665   0.7189   0.4817
  -5.000   0.3210   0.08313   0.07579  -0.0661   0.7096   0.4884
  -4.750   0.2525   0.08378   0.07637  -0.0621   0.7057   0.4974
  -4.500   0.3109   0.08069   0.07324  -0.0639   0.6958   0.4998
  -4.250   0.3478   0.07897   0.07155  -0.0647   0.6850   0.5031
  -4.000   0.3734   0.07764   0.07015  -0.0647   0.6768   0.5077
  -3.750   0.2888   0.07487   0.06726  -0.0619   0.6746   0.4965
  -3.500   0.3106   0.07275   0.06509  -0.0621   0.6674   0.4983
  -3.250   0.3304   0.07114   0.06353  -0.0622   0.6580   0.4991
  -3.000   0.3488   0.06944   0.06179  -0.0622   0.6503   0.5000
  -2.750   0.3699   0.06787   0.06011  -0.0622   0.6441   0.5012
  -2.500   0.3920   0.06693   0.05917  -0.0621   0.6366   0.5034
  -2.250   0.4122   0.06623   0.05853  -0.0617   0.6278   0.5070
  -2.000   0.3262   0.06027   0.05251  -0.0584   0.6254   0.4989
  -1.750   0.4046   0.06173   0.05389  -0.0600   0.6169   0.5046
  -1.500   0.4253   0.06105   0.05314  -0.0597   0.6110   0.5088
  -1.250   0.4238   0.06007   0.05227  -0.0580   0.6033   0.5121
  -1.000   0.4131   0.05836   0.05057  -0.0559   0.5973   0.5151
  -0.750   0.3110   0.05374   0.04593  -0.0483   0.5952   0.5235
  -0.500   0.3674   0.05427   0.04638  -0.0489   0.5889   0.5256
  -0.250   0.4136   0.05480   0.04690  -0.0496   0.5819   0.5285
   0.000   0.4235   0.05483   0.04705  -0.0475   0.5738   0.5317
   0.500   0.3482   0.04821   0.04028  -0.0437   0.5655   0.5506
   0.750   0.3913   0.04853   0.04053  -0.0434   0.5605   0.5524
   1.000   0.4077   0.04944   0.04157  -0.0404   0.5535   0.5546
   1.250   0.4174   0.05003   0.04227  -0.0373   0.5457   0.5577
   1.500   0.4398   0.04967   0.04188  -0.0366   0.5398   0.5621
   1.750   0.4590   0.04804   0.04012  -0.0380   0.5355   0.5688
   2.000   0.4700   0.04534   0.03721  -0.0421   0.5311   0.5800
   2.250   0.4574   0.04646   0.03860  -0.0363   0.5224   0.5822
   2.500   0.4770   0.04670   0.03888  -0.0342   0.5161   0.5849
   2.750   0.5127   0.04629   0.03841  -0.0344   0.5114   0.5885
   3.000   0.5574   0.04569   0.03763  -0.0367   0.5073   0.5936
   3.250   0.5229   0.04683   0.03906  -0.0308   0.4982   0.5990
   3.500   0.5558   0.04559   0.03764  -0.0365   0.4916   0.6087
   3.750   0.5913   0.04468   0.03670  -0.0365   0.4872   0.6120
   4.000   0.6377   0.04417   0.03605  -0.0376   0.4833   0.6156
   4.250   0.5808   0.04686   0.03915  -0.0278   0.4738   0.6180
   4.500   0.5962   0.04709   0.03940  -0.0261   0.4677   0.6222
   4.750   0.6523   0.04583   0.03801  -0.0297   0.4635   0.6284
   5.000   0.7268   0.04427   0.03613  -0.0375   0.4595   0.6364
   5.250   0.5466   0.05268   0.04522  -0.0172   0.4447   0.6356
   5.500   0.6451   0.04855   0.04087  -0.0241   0.4430   0.6433
   5.750   0.7265   0.04636   0.03855  -0.0287   0.4399   0.6485
   6.000   0.8017   0.04488   0.03684  -0.0336   0.4363   0.6539
   6.250   0.5107   0.06486   0.05763  -0.0141   0.4118   0.6494
   6.500   0.5750   0.06075   0.05347  -0.0138   0.4118   0.6555
   6.750   0.6589   0.05597   0.04856  -0.0162   0.4114   0.6635
   7.000   0.4086   0.08585   0.07888  -0.0159   0.3746   0.6554
   7.250   0.4616   0.08300   0.07598  -0.0161   0.3736   0.6622
   7.500   0.5224   0.07972   0.07260  -0.0177   0.3728   0.6704
   8.500   0.7849   0.06154   0.05419  -0.0172   0.3722   0.6992
   8.750   0.9181   0.05326   0.04562  -0.0214   0.3724   0.7083
   9.000   0.4041   0.11510   0.10842  -0.0252   0.3191   0.6838
   9.250   0.4515   0.11264   0.10594  -0.0243   0.3171   0.6907
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