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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 500,000
Max Cl/Cd: 105.67 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-500000.txt
Download as CSV file: xf-hq2590sm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4303   0.08427   0.08200  -0.0388   1.0000   0.0214
  -8.750  -0.4341   0.07953   0.07730  -0.0414   1.0000   0.0215
  -8.500  -0.4397   0.07516   0.07298  -0.0437   1.0000   0.0215
  -8.250  -0.4543   0.07058   0.06846  -0.0463   1.0000   0.0215
  -8.000  -0.4693   0.06637   0.06422  -0.0482   1.0000   0.0215
  -7.750  -0.4758   0.06157   0.05933  -0.0506   0.9985   0.0215
  -7.500  -0.4665   0.05210   0.04971  -0.0600   0.9932   0.0223
  -7.250  -0.4431   0.04885   0.04638  -0.0640   0.9888   0.0229
  -7.000  -0.4159   0.04507   0.04245  -0.0688   0.9853   0.0238
  -6.750  -0.3874   0.04049   0.03762  -0.0734   0.9814   0.0256
  -6.500  -0.3521   0.03737   0.03389  -0.0762   0.9760   0.0283
  -6.250  -0.3290   0.02941   0.02560  -0.0810   0.9726   0.0300
  -6.000  -0.2959   0.02804   0.02420  -0.0836   0.9706   0.0320
  -5.750  -0.2701   0.01776   0.01252  -0.0837   0.9631   0.0229
  -5.500  -0.2376   0.01621   0.01079  -0.0849   0.9591   0.0235
  -5.250  -0.2041   0.01540   0.00989  -0.0863   0.9559   0.0250
  -5.000  -0.1769   0.01442   0.00877  -0.0862   0.9483   0.0261
  -4.750  -0.1468   0.01335   0.00756  -0.0865   0.9431   0.0268
  -4.500  -0.1191   0.01259   0.00669  -0.0864   0.9363   0.0276
  -4.250  -0.0911   0.01211   0.00612  -0.0863   0.9298   0.0283
  -4.000  -0.0656   0.01087   0.00482  -0.0860   0.9230   0.0304
  -3.750  -0.0390   0.01039   0.00431  -0.0858   0.9158   0.0322
  -3.500  -0.0116   0.00999   0.00386  -0.0856   0.9097   0.0341
  -3.250   0.0153   0.00967   0.00348  -0.0854   0.9027   0.0363
  -3.000   0.0423   0.00922   0.00297  -0.0851   0.8958   0.0406
  -2.750   0.0688   0.00897   0.00269  -0.0847   0.8865   0.0473
  -2.500   0.0955   0.00855   0.00231  -0.0844   0.8777   0.0711
  -2.250   0.1218   0.00790   0.00205  -0.0844   0.8700   0.1894
  -2.000   0.1460   0.00678   0.00191  -0.0845   0.8625   0.4916
  -1.750   0.1725   0.00656   0.00188  -0.0841   0.8555   0.5744
  -1.500   0.1993   0.00647   0.00190  -0.0837   0.8483   0.6239
  -1.250   0.2262   0.00644   0.00191  -0.0833   0.8411   0.6657
  -1.000   0.2530   0.00642   0.00192  -0.0828   0.8336   0.6959
  -0.750   0.2800   0.00639   0.00191  -0.0824   0.8265   0.7169
  -0.500   0.3067   0.00638   0.00194  -0.0819   0.8202   0.7424
  -0.250   0.3334   0.00636   0.00196  -0.0815   0.8136   0.7647
   0.000   0.3607   0.00635   0.00195  -0.0812   0.8075   0.7771
   0.250   0.3880   0.00633   0.00196  -0.0809   0.8003   0.7884
   0.500   0.4154   0.00634   0.00195  -0.0807   0.7938   0.8003
   0.750   0.4424   0.00633   0.00197  -0.0803   0.7859   0.8131
   1.000   0.4695   0.00633   0.00198  -0.0800   0.7785   0.8263
   1.250   0.4960   0.00631   0.00200  -0.0795   0.7695   0.8404
   1.500   0.5224   0.00630   0.00202  -0.0790   0.7605   0.8559
   1.750   0.5481   0.00629   0.00204  -0.0784   0.7506   0.8727
   2.000   0.5732   0.00624   0.00205  -0.0775   0.7387   0.8930
   2.250   0.5974   0.00617   0.00204  -0.0765   0.7252   0.9206
   2.500   0.6309   0.00611   0.00200  -0.0775   0.7029   0.9739
   2.750   0.6583   0.00623   0.00198  -0.0773   0.6632   1.0000
   3.000   0.6826   0.00649   0.00200  -0.0766   0.5977   1.0000
   3.250   0.7038   0.00706   0.00216  -0.0754   0.5140   1.0000
   3.500   0.7267   0.00759   0.00241  -0.0746   0.4574   1.0000
   3.750   0.7512   0.00800   0.00264  -0.0741   0.4185   1.0000
   4.000   0.7766   0.00833   0.00285  -0.0737   0.3911   1.0000
   4.250   0.8020   0.00865   0.00307  -0.0734   0.3656   1.0000
   4.500   0.8270   0.00899   0.00331  -0.0730   0.3374   1.0000
   4.750   0.8520   0.00934   0.00354  -0.0726   0.3078   1.0000
   5.000   0.8770   0.00968   0.00378  -0.0722   0.2798   1.0000
   5.250   0.9013   0.01009   0.00405  -0.0717   0.2437   1.0000
   5.500   0.9243   0.01065   0.00439  -0.0711   0.1958   1.0000
   5.750   0.9460   0.01137   0.00482  -0.0703   0.1438   1.0000
   6.000   0.9684   0.01202   0.00529  -0.0696   0.1088   1.0000
   6.250   0.9914   0.01260   0.00575  -0.0689   0.0872   1.0000
   6.500   1.0149   0.01311   0.00622  -0.0683   0.0715   1.0000
   6.750   1.0378   0.01369   0.00672  -0.0676   0.0560   1.0000
   7.000   1.0597   0.01440   0.00735  -0.0667   0.0420   1.0000
   7.250   1.0825   0.01498   0.00796  -0.0659   0.0361   1.0000
   7.500   1.1028   0.01583   0.00882  -0.0648   0.0313   1.0000
   7.750   1.1258   0.01633   0.00939  -0.0641   0.0293   1.0000
   8.000   1.1475   0.01695   0.01006  -0.0632   0.0273   1.0000
   8.250   1.1673   0.01776   0.01090  -0.0620   0.0253   1.0000
   8.500   1.1839   0.01890   0.01213  -0.0604   0.0235   1.0000
   8.750   1.2043   0.01959   0.01292  -0.0593   0.0225   1.0000
   9.000   1.2235   0.02039   0.01380  -0.0581   0.0213   1.0000
   9.250   1.2420   0.02120   0.01466  -0.0568   0.0201   1.0000
   9.500   1.2578   0.02228   0.01579  -0.0553   0.0189   1.0000
   9.750   1.2676   0.02429   0.01793  -0.0529   0.0178   1.0000
  10.000   1.2857   0.02501   0.01878  -0.0516   0.0171   1.0000
  10.250   1.3009   0.02608   0.01996  -0.0499   0.0164   1.0000
  10.500   1.3138   0.02714   0.02114  -0.0479   0.0156   1.0000
  10.750   1.3250   0.02826   0.02235  -0.0458   0.0150   1.0000
  11.000   1.3346   0.02945   0.02362  -0.0435   0.0145   1.0000
  11.250   1.3415   0.03107   0.02531  -0.0412   0.0139   1.0000
  11.500   1.3411   0.03477   0.02926  -0.0386   0.0132   1.0000
  11.750   1.3476   0.03560   0.03024  -0.0363   0.0129   1.0000
  12.000   1.3524   0.03700   0.03181  -0.0342   0.0125   1.0000
  12.250   1.3544   0.03897   0.03398  -0.0322   0.0122   1.0000
  12.500   1.3548   0.04112   0.03631  -0.0303   0.0118   1.0000
  12.750   1.3532   0.04357   0.03893  -0.0287   0.0116   1.0000
  13.000   1.3505   0.04618   0.04172  -0.0274   0.0113   1.0000
  13.250   1.3467   0.04899   0.04468  -0.0265   0.0111   1.0000
  13.500   1.3388   0.05252   0.04840  -0.0259   0.0110   1.0000
  13.750   1.3323   0.05593   0.05196  -0.0259   0.0108   1.0000
  14.000   1.3230   0.05999   0.05618  -0.0264   0.0106   1.0000
  14.250   1.3103   0.06486   0.06123  -0.0276   0.0106   1.0000
  14.500   1.2991   0.06983   0.06635  -0.0294   0.0105   1.0000
  14.750   1.2823   0.07621   0.07293  -0.0324   0.0104   1.0000
  15.000   1.2606   0.08427   0.08121  -0.0368   0.0105   1.0000
  15.250   1.2359   0.09373   0.09091  -0.0426   0.0106   1.0000
  15.500   1.2016   0.10628   0.10372  -0.0506   0.0108   1.0000
  15.750   1.1393   0.12750   0.12531  -0.0646   0.0114   1.0000
  16.000   1.0073   0.17787   0.17585  -0.0927   0.0137   1.0000
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