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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 200,000
Max Cl/Cd: 73.86 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-200000.txt
Download as CSV file: xf-hq2090sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3785   0.09375   0.09040  -0.0257   1.0000   0.0434
  -9.500  -0.4805   0.09672   0.09324  -0.0321   1.0000   0.0403
  -9.250  -0.4727   0.09275   0.08927  -0.0291   1.0000   0.0416
  -9.000  -0.4670   0.08965   0.08616  -0.0291   1.0000   0.0425
  -8.750  -0.4634   0.08643   0.08297  -0.0297   1.0000   0.0436
  -8.500  -0.4626   0.08291   0.07950  -0.0311   1.0000   0.0446
  -8.250  -0.4646   0.07915   0.07578  -0.0330   1.0000   0.0454
  -8.000  -0.4711   0.07511   0.07181  -0.0353   1.0000   0.0464
  -7.750  -0.4797   0.07025   0.06701  -0.0400   1.0000   0.0467
  -7.500  -0.4856   0.06545   0.06218  -0.0434   1.0000   0.0480
  -7.250  -0.4898   0.06119   0.05784  -0.0452   1.0000   0.0492
  -7.000  -0.4982   0.05866   0.05482  -0.0465   1.0000   0.0522
  -6.750  -0.4988   0.05638   0.05228  -0.0448   1.0000   0.0524
  -6.500  -0.5031   0.04920   0.04522  -0.0441   1.0000   0.0539
  -6.250  -0.4976   0.04655   0.04259  -0.0423   1.0000   0.0551
  -6.000  -0.4915   0.04419   0.04018  -0.0406   1.0000   0.0567
  -5.750  -0.4837   0.04172   0.03756  -0.0391   1.0000   0.0590
  -5.500  -0.4747   0.03909   0.03423  -0.0381   1.0000   0.0667
  -5.250  -0.4484   0.02661   0.02044  -0.0365   0.9996   0.0299
  -5.000  -0.4144   0.02467   0.01844  -0.0392   0.9960   0.0338
  -4.750  -0.3786   0.02180   0.01505  -0.0407   0.9930   0.0344
  -4.500  -0.3434   0.01956   0.01242  -0.0419   0.9893   0.0359
  -4.250  -0.3062   0.01825   0.01079  -0.0435   0.9857   0.0394
  -4.000  -0.2695   0.01667   0.00917  -0.0456   0.9829   0.0478
  -3.750  -0.2373   0.01553   0.00799  -0.0466   0.9777   0.0572
  -3.500  -0.2012   0.01467   0.00711  -0.0485   0.9732   0.0695
  -3.250  -0.1622   0.01392   0.00639  -0.0510   0.9699   0.0876
  -3.000  -0.1304   0.01319   0.00577  -0.0522   0.9637   0.1213
  -2.750  -0.1003   0.01113   0.00530  -0.0541   0.9592   0.4676
  -2.500  -0.0648   0.01077   0.00550  -0.0553   0.9558   0.6470
  -2.250  -0.0364   0.01078   0.00553  -0.0551   0.9482   0.6993
  -2.000   0.0007   0.01076   0.00553  -0.0565   0.9441   0.7401
  -1.750   0.0348   0.01073   0.00550  -0.0574   0.9389   0.7708
  -1.500   0.0653   0.01066   0.00545  -0.0574   0.9320   0.7976
  -1.250   0.0992   0.01054   0.00537  -0.0577   0.9278   0.8302
  -1.000   0.1199   0.01046   0.00536  -0.0554   0.9184   0.8607
  -0.750   0.1518   0.01030   0.00519  -0.0555   0.9137   0.8818
  -0.500   0.1763   0.01021   0.00509  -0.0545   0.9045   0.8985
  -0.250   0.2093   0.01005   0.00490  -0.0550   0.8996   0.9142
   0.000   0.2388   0.00996   0.00482  -0.0551   0.8908   0.9318
   0.250   0.2786   0.00977   0.00460  -0.0570   0.8852   0.9475
   0.500   0.3186   0.00959   0.00440  -0.0592   0.8743   0.9639
   0.750   0.3610   0.00941   0.00419  -0.0620   0.8636   0.9802
   1.000   0.4053   0.00926   0.00402  -0.0653   0.8550   0.9978
   1.250   0.4262   0.00924   0.00395  -0.0642   0.8438   1.0000
   1.500   0.4489   0.00926   0.00393  -0.0633   0.8314   1.0000
   1.750   0.4738   0.00928   0.00390  -0.0626   0.8186   1.0000
   2.000   0.4993   0.00929   0.00390  -0.0620   0.8052   1.0000
   2.250   0.5252   0.00931   0.00389  -0.0613   0.7915   1.0000
   2.500   0.5512   0.00934   0.00390  -0.0607   0.7773   1.0000
   2.750   0.5773   0.00938   0.00392  -0.0601   0.7622   1.0000
   3.000   0.6034   0.00941   0.00396  -0.0595   0.7460   1.0000
   3.250   0.6293   0.00947   0.00401  -0.0588   0.7279   1.0000
   3.500   0.6549   0.00952   0.00407  -0.0581   0.7064   1.0000
   3.750   0.6802   0.00959   0.00412  -0.0573   0.6812   1.0000
   4.000   0.7046   0.00969   0.00416  -0.0562   0.6464   1.0000
   4.250   0.7283   0.00986   0.00422  -0.0551   0.6013   1.0000
   4.500   0.7512   0.01017   0.00434  -0.0539   0.5480   1.0000
   4.750   0.7727   0.01065   0.00456  -0.0526   0.4840   1.0000
   5.000   0.7933   0.01129   0.00489  -0.0513   0.4209   1.0000
   5.250   0.8143   0.01194   0.00533  -0.0503   0.3622   1.0000
   5.500   0.8352   0.01265   0.00579  -0.0493   0.3076   1.0000
   5.750   0.8566   0.01335   0.00631  -0.0484   0.2606   1.0000
   6.000   0.8777   0.01409   0.00688  -0.0475   0.2124   1.0000
   6.250   0.8968   0.01511   0.00757  -0.0464   0.1499   1.0000
   6.500   0.9147   0.01636   0.00853  -0.0451   0.1042   1.0000
   6.750   0.9342   0.01741   0.00948  -0.0439   0.0815   1.0000
   7.000   0.9535   0.01847   0.01048  -0.0428   0.0661   1.0000
   7.250   0.9725   0.01958   0.01159  -0.0416   0.0538   1.0000
   7.500   0.9907   0.02091   0.01297  -0.0402   0.0437   1.0000
   7.750   1.0077   0.02264   0.01475  -0.0385   0.0365   1.0000
   8.000   1.0262   0.02394   0.01608  -0.0374   0.0307   1.0000
   8.250   1.0454   0.02626   0.01855  -0.0361   0.0281   1.0000
   8.500   1.0666   0.02816   0.02066  -0.0349   0.0262   1.0000
   8.750   1.0870   0.03035   0.02309  -0.0338   0.0248   1.0000
   9.000   1.1051   0.03220   0.02512  -0.0327   0.0232   1.0000
   9.250   1.1207   0.03466   0.02770  -0.0316   0.0215   1.0000
   9.500   1.1274   0.03981   0.03331  -0.0297   0.0207   1.0000
   9.750   1.1349   0.04261   0.03651  -0.0275   0.0204   1.0000
  10.000   1.1367   0.04613   0.04042  -0.0251   0.0204   1.0000
  10.250   1.1326   0.05021   0.04486  -0.0225   0.0205   1.0000
  10.500   1.1224   0.05432   0.04929  -0.0197   0.0205   1.0000
  10.750   1.1128   0.05804   0.05324  -0.0170   0.0208   1.0000
  11.000   1.1001   0.06091   0.05632  -0.0145   0.0209   1.0000
  11.250   1.0898   0.06353   0.05914  -0.0129   0.0211   1.0000
  11.500   1.0745   0.06709   0.06291  -0.0123   0.0213   1.0000
  11.750   1.0554   0.07145   0.06753  -0.0130   0.0217   1.0000
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