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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.25 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq259b-il-1000000.txt
Download as CSV file: xf-hq259b-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3605   0.08354   0.08197  -0.0358   1.0000   0.0127
  -9.750  -0.3599   0.08004   0.07849  -0.0364   1.0000   0.0128
  -9.500  -0.3586   0.07684   0.07530  -0.0370   1.0000   0.0130
  -9.250  -0.3587   0.07341   0.07188  -0.0376   1.0000   0.0133
  -9.000  -0.3617   0.06944   0.06793  -0.0384   1.0000   0.0135
  -8.750  -0.3670   0.06522   0.06373  -0.0394   1.0000   0.0137
  -8.500  -0.3749   0.06096   0.05951  -0.0403   1.0000   0.0140
  -8.250  -0.3878   0.05715   0.05574  -0.0403   1.0000   0.0140
  -8.000  -0.3962   0.04726   0.04586  -0.0529   0.9924   0.0139
  -7.750  -0.4828   0.02293   0.01968  -0.0796   0.9818   0.0113
  -7.500  -0.4566   0.01927   0.01551  -0.0811   0.9763   0.0119
  -7.250  -0.4271   0.01658   0.01238  -0.0827   0.9723   0.0124
  -7.000  -0.3983   0.01490   0.01052  -0.0838   0.9673   0.0131
  -6.750  -0.3691   0.01446   0.01003  -0.0843   0.9605   0.0137
  -6.500  -0.3390   0.01412   0.00963  -0.0850   0.9544   0.0144
  -6.250  -0.3123   0.01342   0.00880  -0.0849   0.9452   0.0151
  -6.000  -0.2856   0.01271   0.00796  -0.0847   0.9364   0.0157
  -5.750  -0.2587   0.01225   0.00738  -0.0845   0.9276   0.0161
  -5.500  -0.2344   0.01090   0.00586  -0.0840   0.9180   0.0169
  -5.250  -0.2086   0.01027   0.00517  -0.0837   0.9095   0.0178
  -5.000  -0.1819   0.00999   0.00485  -0.0835   0.9008   0.0187
  -4.750  -0.1552   0.00963   0.00443  -0.0833   0.8928   0.0195
  -4.500  -0.1285   0.00925   0.00398  -0.0831   0.8847   0.0202
  -4.250  -0.1015   0.00893   0.00359  -0.0829   0.8771   0.0209
  -4.000  -0.0743   0.00870   0.00329  -0.0827   0.8696   0.0214
  -3.750  -0.0479   0.00812   0.00262  -0.0825   0.8609   0.0233
  -3.500  -0.0208   0.00791   0.00235  -0.0823   0.8516   0.0249
  -3.250   0.0066   0.00772   0.00211  -0.0821   0.8422   0.0265
  -3.000   0.0342   0.00757   0.00191  -0.0820   0.8344   0.0281
  -2.750   0.0618   0.00733   0.00163  -0.0819   0.8268   0.0330
  -2.500   0.0896   0.00714   0.00145  -0.0818   0.8200   0.0434
  -2.250   0.1172   0.00692   0.00131  -0.0818   0.8128   0.0738
  -2.000   0.1447   0.00662   0.00120  -0.0819   0.8061   0.1365
  -1.750   0.1714   0.00597   0.00104  -0.0821   0.7990   0.3057
  -1.500   0.1979   0.00541   0.00097  -0.0822   0.7923   0.4781
  -1.250   0.2254   0.00523   0.00095  -0.0821   0.7851   0.5444
  -1.000   0.2530   0.00514   0.00095  -0.0820   0.7788   0.5894
  -0.750   0.2808   0.00505   0.00097  -0.0819   0.7726   0.6360
  -0.500   0.3085   0.00504   0.00099  -0.0818   0.7667   0.6634
  -0.250   0.3365   0.00502   0.00101  -0.0817   0.7603   0.6833
   0.000   0.3642   0.00502   0.00103  -0.0816   0.7537   0.7084
   0.250   0.3920   0.00501   0.00105  -0.0814   0.7471   0.7250
   0.500   0.4199   0.00501   0.00106  -0.0813   0.7395   0.7351
   0.750   0.4477   0.00502   0.00108  -0.0813   0.7317   0.7445
   1.000   0.4755   0.00504   0.00109  -0.0811   0.7228   0.7545
   1.250   0.5032   0.00505   0.00112  -0.0810   0.7129   0.7654
   1.500   0.5307   0.00507   0.00115  -0.0808   0.7010   0.7767
   1.750   0.5578   0.00510   0.00119  -0.0806   0.6851   0.7889
   2.000   0.5837   0.00520   0.00122  -0.0801   0.6504   0.8029
   2.250   0.6056   0.00562   0.00131  -0.0789   0.5544   0.8189
   2.500   0.6275   0.00615   0.00153  -0.0778   0.4721   0.8367
   2.750   0.6519   0.00644   0.00169  -0.0771   0.4294   0.8556
   3.000   0.6763   0.00665   0.00183  -0.0765   0.3966   0.8764
   3.250   0.7005   0.00679   0.00195  -0.0757   0.3731   0.9022
   3.500   0.7263   0.00684   0.00206  -0.0752   0.3525   0.9544
   3.750   0.7566   0.00708   0.00220  -0.0759   0.3272   1.0000
   4.000   0.7832   0.00730   0.00235  -0.0757   0.3056   1.0000
   4.250   0.8092   0.00758   0.00251  -0.0755   0.2795   1.0000
   4.500   0.8349   0.00788   0.00270  -0.0752   0.2516   1.0000
   4.750   0.8598   0.00826   0.00291  -0.0748   0.2147   1.0000
   5.000   0.8837   0.00876   0.00319  -0.0743   0.1712   1.0000
   5.250   0.9072   0.00931   0.00352  -0.0737   0.1300   1.0000
   5.500   0.9312   0.00979   0.00386  -0.0732   0.1011   1.0000
   5.750   0.9560   0.01018   0.00416  -0.0727   0.0823   1.0000
   6.000   0.9808   0.01056   0.00447  -0.0723   0.0684   1.0000
   6.250   1.0059   0.01091   0.00478  -0.0719   0.0578   1.0000
   6.500   1.0305   0.01130   0.00511  -0.0715   0.0460   1.0000
   6.750   1.0538   0.01184   0.00555  -0.0708   0.0314   1.0000
   7.000   1.0780   0.01227   0.00595  -0.0703   0.0265   1.0000
   7.250   1.1018   0.01275   0.00645  -0.0696   0.0234   1.0000
   7.500   1.1262   0.01312   0.00686  -0.0691   0.0220   1.0000
   7.750   1.1499   0.01356   0.00731  -0.0686   0.0204   1.0000
   8.000   1.1719   0.01420   0.00799  -0.0677   0.0186   1.0000
   8.250   1.1942   0.01478   0.00865  -0.0668   0.0176   1.0000
   8.500   1.2177   0.01519   0.00911  -0.0662   0.0169   1.0000
   8.750   1.2406   0.01564   0.00960  -0.0655   0.0159   1.0000
   9.000   1.2629   0.01614   0.01013  -0.0648   0.0150   1.0000
   9.250   1.2822   0.01695   0.01099  -0.0636   0.0139   1.0000
   9.500   1.2992   0.01795   0.01209  -0.0620   0.0131   1.0000
   9.750   1.3211   0.01840   0.01261  -0.0612   0.0126   1.0000
  10.000   1.3417   0.01895   0.01322  -0.0603   0.0120   1.0000
  10.250   1.3619   0.01951   0.01382  -0.0593   0.0114   1.0000
  10.500   1.3820   0.02003   0.01436  -0.0583   0.0108   1.0000
  10.750   1.3966   0.02099   0.01538  -0.0565   0.0101   1.0000
  11.000   1.4060   0.02235   0.01687  -0.0540   0.0096   1.0000
  11.250   1.4213   0.02298   0.01758  -0.0523   0.0093   1.0000
  11.500   1.4347   0.02364   0.01832  -0.0502   0.0090   1.0000
  11.750   1.4463   0.02440   0.01916  -0.0480   0.0087   1.0000
  12.000   1.4579   0.02517   0.02000  -0.0459   0.0083   1.0000
  12.250   1.4689   0.02599   0.02088  -0.0439   0.0080   1.0000
  12.500   1.4771   0.02704   0.02201  -0.0417   0.0078   1.0000
  12.750   1.4856   0.02809   0.02313  -0.0397   0.0075   1.0000
  13.000   1.4875   0.02970   0.02483  -0.0372   0.0073   1.0000
  13.250   1.4775   0.03243   0.02773  -0.0341   0.0070   1.0000
  13.500   1.4733   0.03486   0.03031  -0.0319   0.0068   1.0000
  13.750   1.4761   0.03675   0.03234  -0.0305   0.0068   1.0000
  14.000   1.4804   0.03857   0.03427  -0.0294   0.0067   1.0000
  14.250   1.4815   0.04081   0.03664  -0.0284   0.0065   1.0000
  14.500   1.4839   0.04301   0.03895  -0.0278   0.0064   1.0000
  14.750   1.4786   0.04622   0.04229  -0.0273   0.0063   1.0000
  15.000   1.4748   0.04942   0.04563  -0.0272   0.0062   1.0000
  15.250   1.4733   0.05252   0.04884  -0.0275   0.0060   1.0000
  15.500   1.4641   0.05687   0.05333  -0.0284   0.0060   1.0000
  15.750   1.4591   0.06093   0.05751  -0.0297   0.0059   1.0000
  16.000   1.4505   0.06589   0.06260  -0.0317   0.0058   1.0000
  16.250   1.4338   0.07270   0.06959  -0.0349   0.0058   1.0000
  16.500   1.4183   0.07981   0.07685  -0.0387   0.0057   1.0000
  16.750   1.4015   0.08754   0.08474  -0.0431   0.0057   1.0000
  17.000   1.3816   0.09616   0.09351  -0.0480   0.0057   1.0000
  17.250   1.3580   0.10574   0.10325  -0.0536   0.0057   1.0000
  17.500   1.3347   0.11551   0.11317  -0.0593   0.0057   1.0000
  17.750   1.3091   0.12610   0.12391  -0.0656   0.0058   1.0000
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