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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 100,000
Max Cl/Cd: 53.48 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-100000-n5.txt
Download as CSV file: xf-hq2090sm-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4646   0.09273   0.08772  -0.0272   1.0000   0.0214
  -9.000  -0.4655   0.08837   0.08342  -0.0293   1.0000   0.0212
  -8.750  -0.4674   0.08391   0.07903  -0.0316   1.0000   0.0211
  -8.500  -0.4704   0.07943   0.07462  -0.0341   1.0000   0.0207
  -8.250  -0.4766   0.07456   0.06983  -0.0373   1.0000   0.0207
  -8.000  -0.4861   0.06895   0.06428  -0.0420   1.0000   0.0200
  -7.750  -0.4931   0.06354   0.05883  -0.0454   1.0000   0.0196
  -7.500  -0.4982   0.05863   0.05384  -0.0471   1.0000   0.0195
  -7.250  -0.5004   0.05428   0.04936  -0.0478   1.0000   0.0198
  -7.000  -0.4998   0.05021   0.04509  -0.0477   1.0000   0.0203
  -6.750  -0.4972   0.04617   0.04080  -0.0471   1.0000   0.0205
  -6.500  -0.4918   0.04235   0.03665  -0.0462   1.0000   0.0213
  -6.250  -0.4838   0.03867   0.03258  -0.0450   1.0000   0.0219
  -6.000  -0.4730   0.03512   0.02857  -0.0437   1.0000   0.0223
  -5.750  -0.4591   0.03192   0.02487  -0.0425   1.0000   0.0226
  -5.500  -0.4424   0.02908   0.02152  -0.0412   1.0000   0.0232
  -5.250  -0.4127   0.02631   0.01818  -0.0420   0.9966   0.0243
  -5.000  -0.3814   0.02391   0.01555  -0.0437   0.9922   0.0272
  -4.750  -0.3475   0.02262   0.01398  -0.0452   0.9876   0.0327
  -4.500  -0.3146   0.02102   0.01207  -0.0460   0.9829   0.0363
  -4.250  -0.2820   0.01973   0.01071  -0.0475   0.9783   0.0460
  -4.000  -0.2502   0.01867   0.00957  -0.0486   0.9731   0.0549
  -3.750  -0.2171   0.01780   0.00862  -0.0499   0.9679   0.0655
  -3.500  -0.1845   0.01708   0.00786  -0.0512   0.9627   0.0791
  -3.250  -0.1520   0.01644   0.00720  -0.0524   0.9569   0.1012
  -3.000  -0.1167   0.01560   0.00658  -0.0545   0.9529   0.1551
  -2.750  -0.0907   0.01424   0.00620  -0.0552   0.9459   0.3666
  -2.500  -0.0618   0.01360   0.00634  -0.0552   0.9409   0.5848
  -2.250  -0.0343   0.01355   0.00638  -0.0547   0.9339   0.6633
  -2.000  -0.0051   0.01352   0.00635  -0.0544   0.9277   0.7169
  -1.750   0.0207   0.01350   0.00636  -0.0533   0.9208   0.7656
  -1.500   0.0457   0.01344   0.00635  -0.0518   0.9140   0.8117
  -1.250   0.0719   0.01336   0.00625  -0.0508   0.9069   0.8411
  -1.000   0.1026   0.01326   0.00607  -0.0511   0.9001   0.8576
  -0.750   0.1333   0.01318   0.00593  -0.0514   0.8930   0.8748
  -0.500   0.1661   0.01308   0.00577  -0.0521   0.8859   0.8931
  -0.250   0.2005   0.01299   0.00563  -0.0533   0.8782   0.9126
   0.000   0.2402   0.01288   0.00548  -0.0555   0.8713   0.9331
   0.250   0.2809   0.01280   0.00537  -0.0582   0.8634   0.9573
   0.500   0.3238   0.01269   0.00522  -0.0612   0.8564   0.9889
   0.750   0.3523   0.01272   0.00520  -0.0617   0.8461   1.0000
   1.000   0.3796   0.01274   0.00517  -0.0616   0.8356   1.0000
   1.250   0.4071   0.01272   0.00511  -0.0614   0.8229   1.0000
   1.500   0.4339   0.01271   0.00505  -0.0609   0.8085   1.0000
   1.750   0.4606   0.01272   0.00503  -0.0604   0.7943   1.0000
   2.000   0.4875   0.01276   0.00508  -0.0601   0.7812   1.0000
   2.250   0.5141   0.01281   0.00513  -0.0596   0.7674   1.0000
   2.500   0.5404   0.01287   0.00519  -0.0591   0.7519   1.0000
   2.750   0.5665   0.01292   0.00526  -0.0585   0.7345   1.0000
   3.000   0.5927   0.01298   0.00535  -0.0578   0.7160   1.0000
   3.250   0.6185   0.01306   0.00546  -0.0572   0.6953   1.0000
   3.500   0.6443   0.01315   0.00557  -0.0565   0.6730   1.0000
   3.750   0.6695   0.01327   0.00571  -0.0557   0.6469   1.0000
   4.000   0.6946   0.01342   0.00589  -0.0549   0.6168   1.0000
   4.250   0.7192   0.01361   0.00606  -0.0539   0.5800   1.0000
   4.500   0.7429   0.01389   0.00622  -0.0528   0.5347   1.0000
   4.750   0.7648   0.01435   0.00644  -0.0515   0.4764   1.0000
   5.000   0.7852   0.01499   0.00678  -0.0501   0.4131   1.0000
   5.250   0.8058   0.01569   0.00729  -0.0489   0.3563   1.0000
   5.500   0.8265   0.01642   0.00782  -0.0479   0.3070   1.0000
   5.750   0.8470   0.01721   0.00842  -0.0469   0.2625   1.0000
   6.000   0.8680   0.01798   0.00908  -0.0460   0.2213   1.0000
   6.250   0.8884   0.01883   0.00978  -0.0451   0.1782   1.0000
   6.500   0.9087   0.01974   0.01058  -0.0442   0.1409   1.0000
   6.750   0.9281   0.02079   0.01150  -0.0432   0.1112   1.0000
   7.000   0.9474   0.02187   0.01258  -0.0421   0.0894   1.0000
   7.250   0.9660   0.02302   0.01375  -0.0409   0.0764   1.0000
   7.500   0.9840   0.02425   0.01504  -0.0396   0.0661   1.0000
   7.750   1.0022   0.02541   0.01624  -0.0385   0.0541   1.0000
   8.000   1.0195   0.02667   0.01759  -0.0373   0.0441   1.0000
   8.250   1.0344   0.02820   0.01913  -0.0360   0.0356   1.0000
   8.500   1.0508   0.02977   0.02095  -0.0344   0.0302   1.0000
   8.750   1.0651   0.03149   0.02278  -0.0328   0.0264   1.0000
   9.000   1.0782   0.03364   0.02514  -0.0312   0.0234   1.0000
   9.250   1.0936   0.03537   0.02714  -0.0298   0.0207   1.0000
   9.500   1.1065   0.03738   0.02935  -0.0283   0.0190   1.0000
   9.750   1.1174   0.03954   0.03168  -0.0267   0.0180   1.0000
  10.000   1.1252   0.04223   0.03456  -0.0251   0.0172   1.0000
  10.250   1.1291   0.04543   0.03805  -0.0230   0.0167   1.0000
  10.500   1.1291   0.04847   0.04147  -0.0206   0.0163   1.0000
  10.750   1.1244   0.05164   0.04500  -0.0182   0.0160   1.0000
  11.000   1.1156   0.05500   0.04870  -0.0163   0.0157   1.0000
  11.250   1.1033   0.05877   0.05279  -0.0150   0.0153   1.0000
  11.500   1.0888   0.06304   0.05735  -0.0147   0.0153   1.0000
  11.750   1.0727   0.06777   0.06234  -0.0154   0.0153   1.0000
  12.000   1.0541   0.07328   0.06809  -0.0173   0.0152   1.0000
  12.250   1.0342   0.07970   0.07472  -0.0205   0.0153   1.0000
  12.500   1.0145   0.08690   0.08209  -0.0248   0.0156   1.0000
  12.750   0.9946   0.09513   0.09046  -0.0303   0.0159   1.0000
  13.000   0.9743   0.10448   0.09992  -0.0366   0.0162   1.0000
  13.250   0.9549   0.11458   0.11008  -0.0432   0.0165   1.0000
  13.500   0.9387   0.12434   0.11987  -0.0490   0.0168   1.0000
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