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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-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-hq259b-il-200000-n5.txt
Download as CSV file: xf-hq259b-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4280   0.09306   0.08937  -0.0336   1.0000   0.0173
  -9.250  -0.4281   0.08935   0.08570  -0.0350   1.0000   0.0175
  -9.000  -0.4356   0.08386   0.08028  -0.0375   1.0000   0.0168
  -8.750  -0.4341   0.08129   0.07775  -0.0381   1.0000   0.0175
  -8.500  -0.4365   0.07814   0.07466  -0.0391   1.0000   0.0185
  -8.250  -0.4479   0.07398   0.07058  -0.0403   1.0000   0.0181
  -8.000  -0.4632   0.06980   0.06650  -0.0419   1.0000   0.0180
  -7.750  -0.4780   0.06443   0.06116  -0.0458   1.0000   0.0178
  -7.500  -0.4704   0.05711   0.05368  -0.0537   0.9943   0.0179
  -7.250  -0.4526   0.04828   0.04449  -0.0625   0.9854   0.0177
  -7.000  -0.4319   0.04083   0.03658  -0.0681   0.9778   0.0178
  -6.750  -0.4068   0.03464   0.02985  -0.0720   0.9720   0.0183
  -6.500  -0.3794   0.02978   0.02439  -0.0746   0.9669   0.0195
  -6.250  -0.3507   0.02615   0.02003  -0.0761   0.9611   0.0210
  -6.000  -0.3200   0.02310   0.01647  -0.0778   0.9573   0.0217
  -5.750  -0.2905   0.02130   0.01445  -0.0789   0.9526   0.0225
  -5.500  -0.2611   0.02017   0.01315  -0.0797   0.9471   0.0237
  -5.250  -0.2292   0.01921   0.01199  -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   0.0276
  -4.500  -0.1386   0.01602   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   0.00486  -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   0.0578
  -2.500   0.0913   0.01170   0.00376  -0.0848   0.8874   0.0818
  -2.000   0.1435   0.00993   0.00339  -0.0854   0.8769   0.4715
  -1.750   0.1693   0.00960   0.00343  -0.0847   0.8697   0.5920
  -1.500   0.1945   0.00950   0.00344  -0.0837   0.8600   0.6528
  -1.250   0.2209   0.00943   0.00339  -0.0829   0.8509   0.6912
  -1.000   0.2457   0.00937   0.00340  -0.0818   0.8419   0.7290
  -0.750   0.2716   0.00933   0.00336  -0.0810   0.8333   0.7527
  -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   0.4050   0.00920   0.00314  -0.0786   0.7918   0.8136
   0.750   0.4313   0.00919   0.00314  -0.0780   0.7834   0.8277
   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   0.5088   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   0.7312   0.9327
   2.250   0.5995   0.00902   0.00312  -0.0769   0.7158   1.0000
   2.500   0.6267   0.00910   0.00319  -0.0767   0.6981   1.0000
   2.750   0.6535   0.00920   0.00324  -0.0764   0.6755   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   0.5811   1.0000
   3.500   0.7223   0.01021   0.00340  -0.0731   0.4932   1.0000
   3.750   0.7428   0.01088   0.00370  -0.0719   0.4326   1.0000
   4.000   0.7660   0.01136   0.00400  -0.0712   0.3951   1.0000
   4.250   0.7904   0.01174   0.00431  -0.0707   0.3711   1.0000
   4.500   0.8149   0.01212   0.00462  -0.0702   0.3472   1.0000
   4.750   0.8393   0.01250   0.00494  -0.0697   0.3234   1.0000
   5.000   0.8635   0.01290   0.00527  -0.0692   0.3005   1.0000
   5.250   0.8879   0.01328   0.00564  -0.0687   0.2763   1.0000
   5.500   0.9108   0.01380   0.00601  -0.0680   0.2380   1.0000
   5.750   0.9314   0.01455   0.00647  -0.0671   0.1814   1.0000
   6.000   0.9514   0.01544   0.00704  -0.0662   0.1319   1.0000
   6.250   0.9730   0.01616   0.00762  -0.0654   0.1054   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   0.0476   1.0000
   7.750   1.1015   0.02032   0.01182  -0.0603   0.0417   1.0000
   8.000   1.1218   0.02107   0.01269  -0.0592   0.0380   1.0000
   8.250   1.1410   0.02190   0.01358  -0.0581   0.0348   1.0000
   8.500   1.1576   0.02298   0.01468  -0.0566   0.0321   1.0000
   8.750   1.1762   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   1.2102   0.02571   0.01777  -0.0527   0.0265   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   0.02936   0.02176  -0.0472   0.0225   1.0000
  10.250   1.2617   0.03053   0.02308  -0.0453   0.0212   1.0000
  10.500   1.2726   0.03166   0.02433  -0.0434   0.0200   1.0000
  10.750   1.2813   0.03300   0.02575  -0.0414   0.0190   1.0000
  11.000   1.2858   0.03502   0.02786  -0.0392   0.0181   1.0000
  11.250   1.2937   0.03674   0.02978  -0.0373   0.0175   1.0000
  11.500   1.3002   0.03856   0.03184  -0.0355   0.0168   1.0000
  11.750   1.3048   0.04049   0.03398  -0.0337   0.0160   1.0000
  12.000   1.3081   0.04248   0.03614  -0.0321   0.0153   1.0000
  12.250   1.3101   0.04454   0.03836  -0.0308   0.0147   1.0000
  12.500   1.3109   0.04674   0.04068  -0.0297   0.0141   1.0000
  12.750   1.3096   0.04933   0.04339  -0.0288   0.0137   1.0000
  13.000   1.3041   0.05269   0.04693  -0.0281   0.0133   1.0000
  13.250   1.2972   0.05640   0.05088  -0.0277   0.0131   1.0000
  13.500   1.2887   0.06047   0.05521  -0.0279   0.0129   1.0000
  13.750   1.2780   0.06507   0.06007  -0.0287   0.0127   1.0000
  14.000   1.2646   0.07037   0.06563  -0.0304   0.0125   1.0000
  14.250   1.2494   0.07635   0.07185  -0.0328   0.0124   1.0000
  14.500   1.2325   0.08319   0.07892  -0.0363   0.0123   1.0000
  14.750   1.2139   0.09097   0.08693  -0.0408   0.0123   1.0000
  15.000   1.1941   0.09964   0.09581  -0.0462   0.0123   1.0000
  15.250   1.1725   0.10930   0.10567  -0.0523   0.0124   1.0000
  15.500   1.1493   0.11987   0.11638  -0.0591   0.0125   1.0000
  15.750   1.1243   0.13152   0.12818  -0.0666   0.0127   1.0000
  16.000   1.0961   0.14493   0.14172  -0.0750   0.0130   1.0000
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