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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 100,000
Max Cl/Cd: 59.4 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1404-il-100000-n5.txt
Download as CSV file: xf-hs1404-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-404 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4745   0.11620   0.11108  -0.0065   1.0000   0.0295
  -8.750  -0.4706   0.11359   0.10852  -0.0089   1.0000   0.0297
  -8.500  -0.4659   0.11072   0.10570  -0.0112   1.0000   0.0299
  -8.250  -0.4610   0.10771   0.10274  -0.0133   1.0000   0.0300
  -8.000  -0.4558   0.10460   0.09968  -0.0153   1.0000   0.0301
  -7.750  -0.4478   0.10115   0.09627  -0.0182   1.0000   0.0301
  -7.500  -0.4381   0.09747   0.09263  -0.0214   1.0000   0.0302
  -7.250  -0.4272   0.09364   0.08882  -0.0245   1.0000   0.0302
  -7.000  -0.4154   0.08969   0.08490  -0.0276   1.0000   0.0302
  -6.750  -0.4026   0.08566   0.08089  -0.0307   1.0000   0.0302
  -6.250  -0.3748   0.07738   0.07262  -0.0368   1.0000   0.0302
  -5.750  -0.3661   0.06975   0.06502  -0.0336   1.0000   0.0351
  -5.500  -0.3279   0.05360   0.04935  -0.0322   1.0000   0.0455
  -5.250  -0.3207   0.05045   0.04622  -0.0322   1.0000   0.0484
  -5.000  -0.3089   0.04657   0.04231  -0.0347   1.0000   0.0487
  -4.750  -0.2788   0.05183   0.04682  -0.0502   1.0000   0.0268
  -4.500  -0.2522   0.04693   0.04178  -0.0540   1.0000   0.0237
  -4.250  -0.2161   0.04048   0.03501  -0.0594   1.0000   0.0207
  -3.750  -0.1488   0.03099   0.02458  -0.0649   1.0000   0.0181
  -3.500  -0.1176   0.02699   0.02005  -0.0669   1.0000   0.0178
  -3.250  -0.0866   0.02379   0.01624  -0.0681   1.0000   0.0176
  -3.000  -0.0563   0.02131   0.01320  -0.0688   1.0000   0.0175
  -2.750  -0.0267   0.01938   0.01083  -0.0691   1.0000   0.0176
  -2.500   0.0024   0.01790   0.00902  -0.0693   1.0000   0.0179
  -2.250   0.0317   0.01669   0.00757  -0.0695   1.0000   0.0186
  -2.000   0.0614   0.01566   0.00622  -0.0699   1.0000   0.0217
  -1.750   0.0905   0.01489   0.00543  -0.0702   1.0000   0.0417
  -1.500   0.1186   0.01435   0.00555  -0.0708   1.0000   0.2023
  -1.250   0.1467   0.01422   0.00532  -0.0711   0.9989   0.2354
  -1.000   0.1816   0.01401   0.00506  -0.0729   0.9953   0.2725
  -0.750   0.2160   0.01372   0.00488  -0.0746   0.9916   0.3293
  -0.500   0.2424   0.01204   0.00466  -0.0741   0.9866   1.0000
  -0.250   0.2798   0.01219   0.00455  -0.0763   0.9815   1.0000
   0.000   0.3148   0.01230   0.00450  -0.0779   0.9741   1.0000
   0.250   0.3527   0.01241   0.00450  -0.0802   0.9686   1.0000
   0.500   0.3862   0.01253   0.00455  -0.0816   0.9610   1.0000
   0.750   0.4247   0.01259   0.00462  -0.0838   0.9539   1.0000
   1.000   0.4653   0.01253   0.00455  -0.0863   0.9434   1.0000
   1.250   0.5015   0.01247   0.00451  -0.0877   0.9307   1.0000
   1.500   0.5336   0.01249   0.00459  -0.0884   0.9195   1.0000
   1.750   0.5649   0.01255   0.00472  -0.0889   0.9092   1.0000
   2.000   0.5962   0.01258   0.00486  -0.0893   0.8984   1.0000
   2.250   0.6267   0.01261   0.00515  -0.0895   0.8862   1.0000
   2.500   0.6560   0.01264   0.00532  -0.0894   0.8720   1.0000
   2.750   0.6847   0.01263   0.00547  -0.0888   0.8542   1.0000
   3.000   0.7105   0.01245   0.00538  -0.0870   0.8147   1.0000
   3.250   0.7318   0.01232   0.00512  -0.0837   0.7278   1.0000
   3.500   0.7505   0.01285   0.00488  -0.0801   0.5428   1.0000
   3.750   0.7652   0.01457   0.00544  -0.0776   0.3309   1.0000
   4.000   0.7819   0.01661   0.00654  -0.0763   0.1230   1.0000
   4.250   0.8029   0.01815   0.00772  -0.0752   0.0697   1.0000
   4.500   0.8257   0.01928   0.00893  -0.0743   0.0523   1.0000
   4.750   0.8473   0.02069   0.01048  -0.0731   0.0446   1.0000
   5.000   0.8690   0.02220   0.01218  -0.0717   0.0390   1.0000
   5.250   0.8913   0.02368   0.01379  -0.0707   0.0303   1.0000
   5.500   0.9144   0.02580   0.01608  -0.0694   0.0253   1.0000
   5.750   0.9380   0.02838   0.01894  -0.0682   0.0197   1.0000
   6.000   0.9619   0.03092   0.02189  -0.0669   0.0154   1.0000
   6.250   0.9833   0.03403   0.02543  -0.0655   0.0136   1.0000
   6.500   1.0006   0.03806   0.02996  -0.0639   0.0126   1.0000
   6.750   1.0104   0.04395   0.03646  -0.0617   0.0118   1.0000
   7.000   1.0280   0.04679   0.04010  -0.0597   0.0102   1.0000
   7.250   1.0385   0.05124   0.04510  -0.0576   0.0089   1.0000
   7.500   1.0447   0.05592   0.05022  -0.0558   0.0081   1.0000
   7.750   1.0467   0.06081   0.05550  -0.0541   0.0077   1.0000
   8.000   1.0444   0.06587   0.06088  -0.0527   0.0076   1.0000
   8.250   1.0380   0.07098   0.06626  -0.0517   0.0076   1.0000
   8.500   1.0276   0.07603   0.07151  -0.0511   0.0077   1.0000
   8.750   1.0123   0.08078   0.07640  -0.0508   0.0078   1.0000
   9.000   0.9967   0.08635   0.08207  -0.0527   0.0081   1.0000
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