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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.23 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-1000000.txt
Download as CSV file: xf-hq2590sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4448   0.08268   0.08105  -0.0364   1.0000   0.0122
  -9.000  -0.4630   0.07549   0.07391  -0.0397   1.0000   0.0124
  -8.750  -0.4680   0.07252   0.07097  -0.0407   1.0000   0.0127
  -8.500  -0.4934   0.06576   0.06428  -0.0436   1.0000   0.0124
  -7.750  -0.4820   0.02345   0.02027  -0.0795   0.9821   0.0113
  -7.500  -0.4570   0.01919   0.01541  -0.0811   0.9764   0.0119
  -7.250  -0.4247   0.01831   0.01433  -0.0824   0.9728   0.0122
  -7.000  -0.3984   0.01485   0.01046  -0.0837   0.9674   0.0131
  -6.750  -0.3693   0.01446   0.01002  -0.0843   0.9605   0.0137
  -6.500  -0.3393   0.01401   0.00951  -0.0850   0.9543   0.0144
  -6.250  -0.3124   0.01339   0.00877  -0.0849   0.9452   0.0151
  -6.000  -0.2857   0.01270   0.00794  -0.0847   0.9364   0.0157
  -5.750  -0.2588   0.01223   0.00735  -0.0845   0.9276   0.0161
  -5.500  -0.2345   0.01089   0.00585  -0.0840   0.9180   0.0169
  -5.250  -0.2087   0.01026   0.00516  -0.0837   0.9095   0.0178
  -5.000  -0.1820   0.00998   0.00484  -0.0835   0.9008   0.0187
  -4.750  -0.1552   0.00963   0.00443  -0.0833   0.8928   0.0195
  -4.500  -0.1285   0.00926   0.00398  -0.0831   0.8848   0.0202
  -4.250  -0.1015   0.00893   0.00359  -0.0829   0.8771   0.0209
  -4.000  -0.0744   0.00870   0.00329  -0.0827   0.8696   0.0214
  -3.750  -0.0479   0.00811   0.00261  -0.0825   0.8608   0.0233
  -3.500  -0.0208   0.00790   0.00235  -0.0823   0.8516   0.0249
  -3.250   0.0065   0.00771   0.00211  -0.0821   0.8423   0.0265
  -3.000   0.0342   0.00757   0.00191  -0.0820   0.8345   0.0281
  -2.750   0.0617   0.00732   0.00163  -0.0819   0.8268   0.0331
  -2.500   0.0895   0.00714   0.00145  -0.0818   0.8200   0.0435
  -2.250   0.1172   0.00692   0.00131  -0.0818   0.8128   0.0739
  -2.000   0.1446   0.00662   0.00120  -0.0819   0.8061   0.1371
  -1.750   0.1713   0.00597   0.00104  -0.0821   0.7989   0.3063
  -1.500   0.1978   0.00541   0.00097  -0.0822   0.7923   0.4793
  -1.250   0.2253   0.00523   0.00095  -0.0821   0.7850   0.5444
  -1.000   0.2529   0.00514   0.00095  -0.0820   0.7788   0.5891
  -0.750   0.2807   0.00505   0.00097  -0.0819   0.7726   0.6358
  -0.500   0.3085   0.00504   0.00099  -0.0818   0.7666   0.6636
  -0.250   0.3365   0.00502   0.00101  -0.0817   0.7604   0.6831
   0.000   0.3642   0.00502   0.00103  -0.0815   0.7537   0.7082
   0.250   0.3919   0.00501   0.00105  -0.0814   0.7472   0.7250
   0.500   0.4198   0.00501   0.00106  -0.0813   0.7395   0.7351
   0.750   0.4477   0.00502   0.00108  -0.0812   0.7317   0.7446
   1.000   0.4754   0.00504   0.00109  -0.0811   0.7228   0.7545
   1.250   0.5032   0.00505   0.00112  -0.0810   0.7128   0.7653
   1.500   0.5306   0.00506   0.00115  -0.0808   0.7011   0.7767
   1.750   0.5577   0.00510   0.00119  -0.0806   0.6850   0.7889
   2.000   0.5836   0.00520   0.00122  -0.0801   0.6500   0.8029
   2.250   0.6055   0.00562   0.00131  -0.0788   0.5536   0.8189
   2.500   0.6274   0.00615   0.00153  -0.0778   0.4723   0.8367
   2.750   0.6518   0.00644   0.00169  -0.0771   0.4297   0.8556
   3.000   0.6762   0.00665   0.00183  -0.0764   0.3965   0.8765
   3.250   0.7004   0.00679   0.00195  -0.0757   0.3730   0.9022
   3.500   0.7262   0.00684   0.00206  -0.0751   0.3523   0.9546
   3.750   0.7564   0.00708   0.00220  -0.0758   0.3269   1.0000
   4.000   0.7830   0.00730   0.00235  -0.0757   0.3057   1.0000
   4.250   0.8090   0.00758   0.00251  -0.0754   0.2795   1.0000
   4.500   0.8348   0.00788   0.00270  -0.0752   0.2518   1.0000
   4.750   0.8596   0.00827   0.00291  -0.0748   0.2143   1.0000
   5.000   0.8835   0.00876   0.00319  -0.0742   0.1712   1.0000
   5.250   0.9070   0.00930   0.00352  -0.0736   0.1303   1.0000
   5.500   0.9310   0.00978   0.00386  -0.0731   0.1010   1.0000
   5.750   0.9558   0.01017   0.00416  -0.0727   0.0824   1.0000
   6.000   0.9806   0.01056   0.00447  -0.0723   0.0684   1.0000
   6.250   1.0056   0.01090   0.00478  -0.0719   0.0579   1.0000
   6.500   1.0302   0.01129   0.00511  -0.0714   0.0461   1.0000
   6.750   1.0535   0.01184   0.00555  -0.0708   0.0314   1.0000
   7.000   1.0777   0.01227   0.00594  -0.0702   0.0266   1.0000
   7.250   1.1015   0.01274   0.00645  -0.0696   0.0235   1.0000
   7.500   1.1259   0.01311   0.00686  -0.0691   0.0220   1.0000
   7.750   1.1496   0.01355   0.00731  -0.0685   0.0204   1.0000
   8.000   1.1717   0.01419   0.00799  -0.0676   0.0186   1.0000
   8.250   1.1938   0.01478   0.00865  -0.0668   0.0176   1.0000
   8.500   1.2174   0.01518   0.00911  -0.0662   0.0169   1.0000
   8.750   1.2403   0.01563   0.00958  -0.0655   0.0159   1.0000
   9.000   1.2626   0.01613   0.01012  -0.0647   0.0150   1.0000
   9.250   1.2820   0.01692   0.01095  -0.0636   0.0139   1.0000
   9.500   1.2987   0.01795   0.01209  -0.0619   0.0131   1.0000
   9.750   1.3205   0.01840   0.01261  -0.0611   0.0126   1.0000
  10.000   1.3412   0.01894   0.01320  -0.0602   0.0120   1.0000
  10.250   1.3614   0.01948   0.01379  -0.0592   0.0114   1.0000
  10.500   1.3814   0.02000   0.01434  -0.0582   0.0108   1.0000
  10.750   1.3962   0.02095   0.01533  -0.0564   0.0101   1.0000
  11.000   1.4052   0.02233   0.01684  -0.0539   0.0096   1.0000
  11.250   1.4221   0.02283   0.01742  -0.0523   0.0093   1.0000
  11.500   1.4341   0.02358   0.01826  -0.0501   0.0090   1.0000
  11.750   1.4461   0.02432   0.01907  -0.0479   0.0086   1.0000
  12.000   1.4576   0.02509   0.01991  -0.0458   0.0083   1.0000
  12.250   1.4674   0.02600   0.02089  -0.0436   0.0080   1.0000
  12.500   1.4772   0.02692   0.02188  -0.0416   0.0077   1.0000
  12.750   1.4846   0.02806   0.02310  -0.0395   0.0075   1.0000
  13.000   1.4870   0.02963   0.02476  -0.0371   0.0073   1.0000
  13.250   1.4766   0.03240   0.02770  -0.0339   0.0070   1.0000
  13.500   1.4710   0.03495   0.03042  -0.0316   0.0068   1.0000
  13.750   1.4783   0.03642   0.03199  -0.0305   0.0067   1.0000
  14.000   1.4806   0.03843   0.03412  -0.0293   0.0066   1.0000
  14.250   1.4815   0.04068   0.03649  -0.0283   0.0065   1.0000
  14.500   1.4821   0.04308   0.03902  -0.0276   0.0064   1.0000
  14.750   1.4780   0.04615   0.04222  -0.0271   0.0063   1.0000
  15.000   1.4773   0.04898   0.04517  -0.0271   0.0061   1.0000
  15.250   1.4693   0.05288   0.04922  -0.0274   0.0061   1.0000
  15.500   1.4643   0.05668   0.05314  -0.0282   0.0060   1.0000
  15.750   1.4548   0.06141   0.05801  -0.0297   0.0059   1.0000
  16.000   1.4461   0.06643   0.06317  -0.0318   0.0058   1.0000
  16.250   1.4322   0.07279   0.06968  -0.0348   0.0058   1.0000
  16.500   1.4173   0.07979   0.07683  -0.0386   0.0057   1.0000
  16.750   1.4013   0.08738   0.08457  -0.0429   0.0057   1.0000
  17.000   1.3826   0.09574   0.09308  -0.0477   0.0057   1.0000
  17.250   1.3559   0.10595   0.10346  -0.0536   0.0057   1.0000
  17.500   1.3353   0.11515   0.11280  -0.0590   0.0057   1.0000
  17.750   1.3068   0.12637   0.12419  -0.0657   0.0058   1.0000
  18.000   1.2799   0.13775   0.13573  -0.0726   0.0058   1.0000
  18.250   1.2530   0.14960   0.14773  -0.0800   0.0059   1.0000
  18.500   1.2185   0.16414   0.16245  -0.0890   0.0060   1.0000
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