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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 200,000
Max Cl/Cd: 73.58 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-200000-n5.txt
Download as CSV file: xf-hq2590sm-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4296   0.09260   0.08891  -0.0339   1.0000   0.0170
  -9.250  -0.4313   0.08843   0.08480  -0.0355   1.0000   0.0170
  -9.000  -0.4349   0.08409   0.08050  -0.0373   1.0000   0.0169
  -8.750  -0.4337   0.08141   0.07787  -0.0380   1.0000   0.0176
  -8.500  -0.4376   0.07791   0.07443  -0.0392   1.0000   0.0182
  -8.250  -0.4482   0.07394   0.07054  -0.0403   1.0000   0.0181
  -8.000  -0.4626   0.06993   0.06664  -0.0418   1.0000   0.0182
  -7.750  -0.4784   0.06433   0.06106  -0.0459   1.0000   0.0178
  -7.500  -0.4704   0.05710   0.05367  -0.0537   0.9943   0.0180
  -7.250  -0.4526   0.04822   0.04443  -0.0626   0.9854   0.0177
  -7.000  -0.4319   0.04089   0.03664  -0.0680   0.9779   0.0178
  -6.750  -0.4068   0.03466   0.02987  -0.0720   0.9720   0.0183
  -6.500  -0.3793   0.02981   0.02442  -0.0746   0.9670   0.0195
  -6.250  -0.3508   0.02616   0.02004  -0.0761   0.9611   0.0210
  -6.000  -0.3201   0.02310   0.01647  -0.0778   0.9573   0.0217
  -5.750  -0.2905   0.02128   0.01442  -0.0789   0.9526   0.0225
  -5.500  -0.2612   0.02018   0.01316  -0.0797   0.9471   0.0237
  -5.250  -0.2292   0.01920   0.01200  -0.0808   0.9433   0.0255
  -5.000  -0.1981   0.01797   0.01053  -0.0816   0.9392   0.0267
  -4.750  -0.1697   0.01691   0.00931  -0.0817   0.9332   0.0275
  -4.500  -0.1386   0.01603   0.00829  -0.0824   0.9289   0.0284
  -4.250  -0.1095   0.01499   0.00721  -0.0829   0.9240   0.0303
  -4.000  -0.0814   0.01443   0.00663  -0.0831   0.9179   0.0327
  -3.750  -0.0512   0.01383   0.00598  -0.0837   0.9136   0.0347
  -3.500  -0.0227   0.01332   0.00540  -0.0839   0.9084   0.0369
  -3.250   0.0055   0.01285   0.00485  -0.0841   0.9027   0.0398
  -3.000   0.0354   0.01241   0.00439  -0.0846   0.8984   0.0463
  -2.750   0.0631   0.01206   0.00406  -0.0846   0.8925   0.0579
  -2.500   0.0913   0.01170   0.00376  -0.0848   0.8874   0.0817
  -2.250   0.1200   0.01113   0.00348  -0.0853   0.8835   0.1662
  -2.000   0.1435   0.00993   0.00339  -0.0854   0.8770   0.4698
  -1.750   0.1693   0.00960   0.00343  -0.0847   0.8697   0.5923
  -1.500   0.1945   0.00950   0.00344  -0.0837   0.8600   0.6527
  -1.250   0.2209   0.00943   0.00339  -0.0829   0.8509   0.6913
  -1.000   0.2458   0.00937   0.00340  -0.0818   0.8419   0.7289
  -0.750   0.2716   0.00933   0.00336  -0.0810   0.8333   0.7528
  -0.500   0.2987   0.00928   0.00326  -0.0805   0.8249   0.7642
  -0.250   0.3249   0.00925   0.00322  -0.0800   0.8150   0.7757
   0.000   0.3519   0.00923   0.00317  -0.0795   0.8073   0.7875
   0.250   0.3783   0.00921   0.00316  -0.0791   0.7993   0.8001
   0.500   0.4051   0.00920   0.00314  -0.0786   0.7918   0.8136
   0.750   0.4313   0.00919   0.00314  -0.0780   0.7833   0.8278
   1.000   0.4571   0.00917   0.00315  -0.0774   0.7746   0.8430
   1.250   0.4832   0.00915   0.00313  -0.0767   0.7657   0.8599
   1.500   0.5089   0.00912   0.00314  -0.0760   0.7551   0.8791
   1.750   0.5351   0.00909   0.00315  -0.0754   0.7438   0.9019
   2.000   0.5649   0.00903   0.00313  -0.0756   0.7313   0.9328
   2.250   0.5995   0.00902   0.00312  -0.0769   0.7158   1.0000
   2.500   0.6267   0.00910   0.00319  -0.0767   0.6982   1.0000
   2.750   0.6535   0.00920   0.00324  -0.0764   0.6757   1.0000
   3.000   0.6795   0.00932   0.00329  -0.0759   0.6425   1.0000
   3.250   0.7034   0.00956   0.00330  -0.0749   0.5808   1.0000
   3.500   0.7224   0.01021   0.00340  -0.0731   0.4936   1.0000
   3.750   0.7428   0.01088   0.00370  -0.0719   0.4324   1.0000
   4.000   0.7660   0.01135   0.00400  -0.0712   0.3952   1.0000
   4.250   0.7905   0.01174   0.00431  -0.0707   0.3711   1.0000
   4.500   0.8149   0.01212   0.00462  -0.0702   0.3475   1.0000
   4.750   0.8393   0.01250   0.00494  -0.0697   0.3233   1.0000
   5.000   0.8635   0.01290   0.00527  -0.0692   0.3004   1.0000
   5.250   0.8879   0.01328   0.00564  -0.0687   0.2762   1.0000
   5.500   0.9108   0.01380   0.00601  -0.0680   0.2385   1.0000
   5.750   0.9314   0.01455   0.00647  -0.0671   0.1811   1.0000
   6.000   0.9515   0.01543   0.00704  -0.0662   0.1323   1.0000
   6.250   0.9730   0.01616   0.00763  -0.0654   0.1053   1.0000
   6.500   0.9953   0.01678   0.00823  -0.0647   0.0889   1.0000
   6.750   1.0175   0.01742   0.00885  -0.0639   0.0762   1.0000
   7.000   1.0391   0.01811   0.00952  -0.0631   0.0653   1.0000
   7.250   1.0608   0.01876   0.01021  -0.0623   0.0557   1.0000
   7.500   1.0820   0.01946   0.01097  -0.0614   0.0477   1.0000
   7.750   1.1015   0.02032   0.01182  -0.0603   0.0417   1.0000
   8.000   1.1218   0.02107   0.01269  -0.0593   0.0380   1.0000
   8.250   1.1410   0.02190   0.01359  -0.0581   0.0348   1.0000
   8.500   1.1576   0.02297   0.01468  -0.0567   0.0321   1.0000
   8.750   1.1763   0.02382   0.01568  -0.0554   0.0301   1.0000
   9.000   1.1935   0.02477   0.01674  -0.0540   0.0283   1.0000
   9.250   1.2103   0.02571   0.01777  -0.0527   0.0266   1.0000
   9.500   1.2237   0.02693   0.01904  -0.0510   0.0248   1.0000
   9.750   1.2366   0.02820   0.02043  -0.0491   0.0236   1.0000
  10.000   1.2496   0.02937   0.02176  -0.0472   0.0225   1.0000
  10.250   1.2617   0.03053   0.02309  -0.0453   0.0212   1.0000
  10.500   1.2726   0.03170   0.02437  -0.0434   0.0200   1.0000
  10.750   1.2813   0.03300   0.02576  -0.0414   0.0190   1.0000
  11.000   1.2860   0.03501   0.02785  -0.0392   0.0181   1.0000
  11.250   1.2938   0.03673   0.02977  -0.0373   0.0175   1.0000
  11.500   1.3002   0.03857   0.03185  -0.0355   0.0168   1.0000
  11.750   1.3049   0.04049   0.03398  -0.0337   0.0160   1.0000
  12.000   1.3082   0.04248   0.03615  -0.0321   0.0153   1.0000
  12.250   1.3103   0.04448   0.03829  -0.0308   0.0146   1.0000
  12.500   1.3111   0.04673   0.04066  -0.0297   0.0141   1.0000
  12.750   1.3096   0.04935   0.04341  -0.0288   0.0137   1.0000
  13.000   1.3041   0.05271   0.04695  -0.0281   0.0133   1.0000
  13.250   1.2973   0.05640   0.05088  -0.0278   0.0131   1.0000
  13.500   1.2889   0.06046   0.05521  -0.0280   0.0129   1.0000
  13.750   1.2780   0.06508   0.06009  -0.0288   0.0127   1.0000
  14.000   1.2645   0.07041   0.06567  -0.0304   0.0125   1.0000
  14.250   1.2495   0.07638   0.07188  -0.0329   0.0124   1.0000
  14.500   1.2325   0.08323   0.07896  -0.0364   0.0123   1.0000
  14.750   1.2143   0.09094   0.08690  -0.0408   0.0123   1.0000
  15.000   1.1942   0.09968   0.09585  -0.0462   0.0123   1.0000
  15.250   1.1725   0.10937   0.10574  -0.0524   0.0124   1.0000
  15.500   1.1495   0.11989   0.11640  -0.0591   0.0126   1.0000
  15.750   1.1241   0.13169   0.12835  -0.0667   0.0127   1.0000
  16.000   1.0960   0.14509   0.14188  -0.0751   0.0130   1.0000
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