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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 500,000
Max Cl/Cd: 105.7 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq259b-il-500000.txt
Download as CSV file: xf-hq259b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 B AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3465   0.08574   0.08354  -0.0378   1.0000   0.0214
  -9.500  -0.3490   0.08112   0.07894  -0.0393   1.0000   0.0215
  -9.250  -0.3520   0.07654   0.07439  -0.0406   1.0000   0.0215
  -9.000  -0.3657   0.07014   0.06803  -0.0412   1.0000   0.0221
  -8.750  -0.3688   0.06645   0.06436  -0.0416   1.0000   0.0223
  -8.500  -0.3692   0.06378   0.06173  -0.0411   1.0000   0.0227
  -8.250  -0.3817   0.05929   0.05728  -0.0421   1.0000   0.0226
  -8.000  -0.4071   0.05586   0.05393  -0.0409   1.0000   0.0225
  -7.750  -0.4759   0.06174   0.05951  -0.0503   0.9986   0.0215
  -7.500  -0.4665   0.05215   0.04976  -0.0599   0.9933   0.0223
  -7.250  -0.4432   0.04867   0.04620  -0.0642   0.9888   0.0229
  -7.000  -0.4160   0.04493   0.04230  -0.0688   0.9853   0.0238
  -6.750  -0.3874   0.04046   0.03759  -0.0734   0.9815   0.0257
  -6.500  -0.3521   0.03732   0.03384  -0.0763   0.9760   0.0283
  -5.750  -0.2700   0.01787   0.01265  -0.0837   0.9631   0.0230
  -5.500  -0.2376   0.01628   0.01086  -0.0850   0.9592   0.0236
  -5.250  -0.2041   0.01545   0.00994  -0.0863   0.9559   0.0250
  -5.000  -0.1768   0.01443   0.00877  -0.0862   0.9483   0.0261
  -4.750  -0.1468   0.01335   0.00756  -0.0866   0.9431   0.0268
  -4.500  -0.1191   0.01259   0.00668  -0.0864   0.9363   0.0276
  -4.250  -0.0911   0.01209   0.00610  -0.0863   0.9298   0.0283
  -4.000  -0.0655   0.01088   0.00483  -0.0861   0.9230   0.0304
  -3.750  -0.0389   0.01039   0.00431  -0.0858   0.9158   0.0321
  -3.500  -0.0116   0.01000   0.00386  -0.0856   0.9097   0.0341
  -3.250   0.0153   0.00967   0.00349  -0.0854   0.9027   0.0363
  -3.000   0.0424   0.00922   0.00297  -0.0852   0.8959   0.0406
  -2.750   0.0689   0.00897   0.00269  -0.0847   0.8865   0.0473
  -2.500   0.0956   0.00855   0.00231  -0.0844   0.8777   0.0711
  -2.250   0.1218   0.00790   0.00205  -0.0844   0.8700   0.1884
  -2.000   0.1461   0.00678   0.00191  -0.0845   0.8625   0.4910
  -1.750   0.1726   0.00656   0.00188  -0.0841   0.8555   0.5744
  -1.500   0.1994   0.00647   0.00190  -0.0837   0.8483   0.6240
  -1.250   0.2262   0.00644   0.00191  -0.0833   0.8411   0.6659
  -1.000   0.2531   0.00642   0.00192  -0.0828   0.8337   0.6958
  -0.750   0.2800   0.00639   0.00191  -0.0824   0.8265   0.7170
  -0.500   0.3068   0.00638   0.00194  -0.0820   0.8202   0.7424
  -0.250   0.3334   0.00636   0.00196  -0.0815   0.8136   0.7647
   0.000   0.3608   0.00635   0.00195  -0.0812   0.8075   0.7770
   0.250   0.3881   0.00633   0.00196  -0.0809   0.8004   0.7884
   0.500   0.4154   0.00634   0.00195  -0.0807   0.7938   0.8003
   0.750   0.4425   0.00633   0.00197  -0.0804   0.7859   0.8131
   1.250   0.4961   0.00631   0.00200  -0.0796   0.7695   0.8404
   1.500   0.5225   0.00630   0.00202  -0.0791   0.7605   0.8559
   1.750   0.5482   0.00629   0.00204  -0.0784   0.7506   0.8728
   2.000   0.5732   0.00624   0.00205  -0.0776   0.7387   0.8930
   2.250   0.5975   0.00617   0.00204  -0.0765   0.7252   0.9206
   2.500   0.6311   0.00611   0.00200  -0.0775   0.7033   0.9739
   2.750   0.6585   0.00623   0.00198  -0.0774   0.6636   1.0000
   3.000   0.6827   0.00649   0.00200  -0.0766   0.5974   1.0000
   3.250   0.7039   0.00706   0.00216  -0.0754   0.5139   1.0000
   3.500   0.7269   0.00760   0.00241  -0.0746   0.4571   1.0000
   3.750   0.7514   0.00800   0.00264  -0.0741   0.4185   1.0000
   4.000   0.7767   0.00833   0.00286  -0.0738   0.3910   1.0000
   4.250   0.8022   0.00865   0.00307  -0.0734   0.3658   1.0000
   4.500   0.8273   0.00899   0.00331  -0.0731   0.3379   1.0000
   4.750   0.8522   0.00934   0.00354  -0.0726   0.3075   1.0000
   5.000   0.8772   0.00969   0.00378  -0.0723   0.2797   1.0000
   5.250   0.9015   0.01010   0.00405  -0.0718   0.2433   1.0000
   5.500   0.9246   0.01066   0.00439  -0.0711   0.1958   1.0000
   5.750   0.9463   0.01137   0.00483  -0.0703   0.1436   1.0000
   6.000   0.9687   0.01203   0.00529  -0.0696   0.1087   1.0000
   6.250   0.9917   0.01260   0.00576  -0.0690   0.0871   1.0000
   6.500   1.0152   0.01312   0.00622  -0.0684   0.0714   1.0000
   6.750   1.0382   0.01369   0.00673  -0.0677   0.0559   1.0000
   7.000   1.0600   0.01442   0.00736  -0.0668   0.0419   1.0000
   7.250   1.0828   0.01499   0.00796  -0.0660   0.0360   1.0000
   7.500   1.1032   0.01584   0.00882  -0.0649   0.0313   1.0000
   7.750   1.1262   0.01634   0.00939  -0.0641   0.0293   1.0000
   8.000   1.1480   0.01696   0.01006  -0.0632   0.0273   1.0000
   8.250   1.1676   0.01779   0.01092  -0.0621   0.0252   1.0000
   8.500   1.1843   0.01892   0.01215  -0.0604   0.0235   1.0000
   8.750   1.2049   0.01959   0.01292  -0.0594   0.0224   1.0000
   9.000   1.2240   0.02040   0.01381  -0.0582   0.0213   1.0000
   9.250   1.2424   0.02122   0.01469  -0.0569   0.0201   1.0000
   9.500   1.2582   0.02229   0.01580  -0.0553   0.0189   1.0000
   9.750   1.2682   0.02428   0.01792  -0.0530   0.0177   1.0000
  10.000   1.2861   0.02503   0.01881  -0.0517   0.0171   1.0000
  10.250   1.3016   0.02607   0.01996  -0.0500   0.0163   1.0000
  10.500   1.3143   0.02719   0.02119  -0.0480   0.0156   1.0000
  10.750   1.3256   0.02827   0.02236  -0.0459   0.0150   1.0000
  11.000   1.3352   0.02949   0.02367  -0.0437   0.0145   1.0000
  11.250   1.3427   0.03102   0.02528  -0.0414   0.0140   1.0000
  11.500   1.3417   0.03494   0.02943  -0.0387   0.0132   1.0000
  11.750   1.3478   0.03579   0.03044  -0.0364   0.0130   1.0000
  12.000   1.3531   0.03703   0.03184  -0.0343   0.0125   1.0000
  12.250   1.3555   0.03890   0.03391  -0.0323   0.0121   1.0000
  12.500   1.3551   0.04124   0.03644  -0.0304   0.0119   1.0000
  12.750   1.3538   0.04362   0.03899  -0.0288   0.0116   1.0000
  13.000   1.3504   0.04633   0.04187  -0.0275   0.0113   1.0000
  13.250   1.3462   0.04921   0.04492  -0.0266   0.0111   1.0000
  13.500   1.3400   0.05247   0.04835  -0.0260   0.0110   1.0000
  13.750   1.3307   0.05634   0.05240  -0.0260   0.0108   1.0000
  14.000   1.3214   0.06040   0.05662  -0.0266   0.0107   1.0000
  14.250   1.3102   0.06504   0.06142  -0.0278   0.0106   1.0000
  14.500   1.2967   0.07040   0.06696  -0.0297   0.0105   1.0000
  14.750   1.2815   0.07654   0.07327  -0.0326   0.0104   1.0000
  15.000   1.2615   0.08426   0.08121  -0.0369   0.0105   1.0000
  15.250   1.2355   0.09400   0.09118  -0.0428   0.0106   1.0000
  15.500   1.2028   0.10619   0.10363  -0.0506   0.0108   1.0000
  15.750   1.1383   0.12799   0.12580  -0.0650   0.0114   1.0000
  16.000   1.0098   0.17696   0.17495  -0.0924   0.0137   1.0000
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