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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.33 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259b-il-1000000-n5.txt
Download as CSV file: xf-hq259b-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.5064   0.15188   0.15006  -0.0082   1.0000   0.0038
 -13.750  -0.5029   0.14779   0.14597  -0.0096   1.0000   0.0039
 -11.750  -0.9005   0.02977   0.02718  -0.0713   1.0000   0.0052
 -11.500  -0.8957   0.02658   0.02369  -0.0706   0.9997   0.0054
 -11.250  -0.8726   0.02399   0.02081  -0.0726   0.9971   0.0055
 -11.000  -0.8473   0.02205   0.01862  -0.0741   0.9940   0.0057
 -10.750  -0.8224   0.02046   0.01681  -0.0751   0.9903   0.0058
 -10.500  -0.7951   0.01909   0.01526  -0.0763   0.9869   0.0060
 -10.250  -0.7657   0.01804   0.01408  -0.0776   0.9843   0.0064
 -10.000  -0.7351   0.01754   0.01354  -0.0788   0.9817   0.0067
  -9.750  -0.7062   0.01702   0.01295  -0.0795   0.9775   0.0070
  -9.500  -0.6757   0.01646   0.01232  -0.0806   0.9736   0.0073
  -9.250  -0.6444   0.01578   0.01153  -0.0819   0.9700   0.0077
  -9.000  -0.6157   0.01504   0.01067  -0.0826   0.9639   0.0080
  -8.750  -0.5858   0.01436   0.00986  -0.0835   0.9575   0.0083
  -8.500  -0.5574   0.01378   0.00916  -0.0840   0.9496   0.0085
  -8.000  -0.5026   0.01285   0.00809  -0.0844   0.9315   0.0093
  -7.750  -0.4756   0.01255   0.00773  -0.0843   0.9224   0.0097
  -7.500  -0.4490   0.01229   0.00740  -0.0842   0.9129   0.0102
  -7.250  -0.4225   0.01200   0.00702  -0.0841   0.9035   0.0107
  -7.000  -0.3961   0.01167   0.00660  -0.0839   0.8947   0.0112
  -6.750  -0.3697   0.01135   0.00618  -0.0837   0.8856   0.0115
  -6.500  -0.3430   0.01107   0.00581  -0.0835   0.8772   0.0117
  -6.000  -0.2906   0.01013   0.00472  -0.0832   0.8610   0.0129
  -5.500  -0.2364   0.00965   0.00414  -0.0830   0.8473   0.0140
  -5.250  -0.2094   0.00937   0.00380  -0.0829   0.8407   0.0145
  -5.000  -0.1820   0.00911   0.00348  -0.0828   0.8348   0.0150
  -4.750  -0.1545   0.00891   0.00322  -0.0827   0.8285   0.0155
  -4.500  -0.1270   0.00874   0.00300  -0.0827   0.8228   0.0158
  -4.250  -0.0996   0.00839   0.00260  -0.0827   0.8168   0.0165
  -4.000  -0.0721   0.00817   0.00231  -0.0826   0.8107   0.0173
  -3.750  -0.0444   0.00799   0.00210  -0.0825   0.8027   0.0181
  -3.500  -0.0170   0.00785   0.00191  -0.0824   0.7925   0.0190
  -3.250   0.0105   0.00773   0.00173  -0.0823   0.7825   0.0200
  -3.000   0.0384   0.00763   0.00159  -0.0823   0.7745   0.0211
  -2.750   0.0661   0.00750   0.00143  -0.0822   0.7669   0.0241
  -2.500   0.0941   0.00738   0.00131  -0.0822   0.7599   0.0279
  -2.250   0.1219   0.00728   0.00120  -0.0822   0.7527   0.0360
  -2.000   0.1499   0.00716   0.00112  -0.0822   0.7456   0.0490
  -1.750   0.1777   0.00706   0.00104  -0.0822   0.7380   0.0652
  -1.500   0.2057   0.00691   0.00097  -0.0822   0.7307   0.0951
  -1.000   0.2604   0.00615   0.00080  -0.0826   0.7145   0.3155
  -0.750   0.2872   0.00565   0.00077  -0.0827   0.7074   0.4869
  -0.500   0.3150   0.00549   0.00077  -0.0827   0.6999   0.5476
  -0.250   0.3426   0.00542   0.00079  -0.0826   0.6914   0.5877
   0.000   0.3703   0.00536   0.00083  -0.0825   0.6816   0.6308
   0.250   0.3979   0.00535   0.00086  -0.0824   0.6698   0.6610
   0.500   0.4255   0.00540   0.00088  -0.0823   0.6541   0.6716
   0.750   0.4528   0.00549   0.00089  -0.0821   0.6306   0.6799
   1.000   0.4783   0.00571   0.00094  -0.0816   0.5782   0.6875
   1.250   0.5028   0.00609   0.00106  -0.0810   0.5125   0.6953
   1.500   0.5281   0.00640   0.00119  -0.0806   0.4647   0.7031
   1.750   0.5538   0.00668   0.00131  -0.0802   0.4237   0.7106
   2.000   0.5792   0.00698   0.00145  -0.0799   0.3796   0.7184
   2.250   0.6052   0.00723   0.00157  -0.0795   0.3465   0.7268
   2.500   0.6315   0.00742   0.00169  -0.0793   0.3219   0.7363
   2.750   0.6579   0.00760   0.00181  -0.0791   0.3012   0.7455
   3.000   0.6846   0.00775   0.00193  -0.0789   0.2854   0.7556
   3.250   0.7109   0.00792   0.00207  -0.0786   0.2640   0.7679
   3.500   0.7366   0.00815   0.00223  -0.0783   0.2387   0.7820
   3.750   0.7622   0.00836   0.00239  -0.0779   0.2156   0.7974
   4.000   0.7873   0.00862   0.00259  -0.0774   0.1889   0.8144
   4.250   0.8105   0.00906   0.00288  -0.0767   0.1453   0.8343
   4.500   0.8342   0.00942   0.00314  -0.0760   0.1144   0.8556
   4.750   0.8582   0.00968   0.00338  -0.0753   0.0950   0.8782
   5.000   0.8811   0.00992   0.00362  -0.0744   0.0781   0.9082
   5.250   0.9094   0.01011   0.00386  -0.0746   0.0654   1.0000
   5.500   0.9353   0.01038   0.00409  -0.0743   0.0582   1.0000
   5.750   0.9610   0.01065   0.00434  -0.0741   0.0519   1.0000
   6.000   0.9865   0.01095   0.00461  -0.0737   0.0449   1.0000
   6.250   1.0117   0.01126   0.00490  -0.0734   0.0376   1.0000
   6.500   1.0363   0.01165   0.00523  -0.0729   0.0289   1.0000
   6.750   1.0610   0.01202   0.00557  -0.0725   0.0239   1.0000
   7.000   1.0858   0.01235   0.00590  -0.0721   0.0217   1.0000
   7.250   1.1102   0.01273   0.00628  -0.0716   0.0198   1.0000
   7.500   1.1344   0.01312   0.00669  -0.0710   0.0180   1.0000
   7.750   1.1590   0.01344   0.00705  -0.0706   0.0174   1.0000
   8.000   1.1832   0.01379   0.00743  -0.0701   0.0166   1.0000
   8.250   1.2070   0.01417   0.00785  -0.0696   0.0158   1.0000
   8.500   1.2303   0.01459   0.00829  -0.0689   0.0148   1.0000
   8.750   1.2527   0.01510   0.00882  -0.0682   0.0136   1.0000
   9.000   1.2755   0.01554   0.00930  -0.0675   0.0131   1.0000
   9.250   1.2986   0.01592   0.00974  -0.0669   0.0126   1.0000
   9.500   1.3212   0.01633   0.01020  -0.0662   0.0120   1.0000
   9.750   1.3433   0.01677   0.01068  -0.0655   0.0112   1.0000
  10.000   1.3648   0.01725   0.01117  -0.0647   0.0104   1.0000
  10.250   1.3852   0.01782   0.01177  -0.0637   0.0095   1.0000
  10.500   1.4063   0.01827   0.01228  -0.0628   0.0089   1.0000
  10.750   1.4265   0.01879   0.01284  -0.0618   0.0083   1.0000
  11.000   1.4458   0.01935   0.01343  -0.0607   0.0076   1.0000
  11.250   1.4638   0.01999   0.01411  -0.0594   0.0069   1.0000
  11.500   1.4811   0.02063   0.01481  -0.0580   0.0065   1.0000
  11.750   1.4968   0.02127   0.01552  -0.0563   0.0061   1.0000
  12.000   1.5101   0.02194   0.01626  -0.0543   0.0058   1.0000
  12.250   1.5221   0.02267   0.01704  -0.0521   0.0054   1.0000
  12.500   1.5330   0.02348   0.01791  -0.0498   0.0051   1.0000
  12.750   1.5425   0.02440   0.01890  -0.0475   0.0048   1.0000
  13.000   1.5506   0.02543   0.02003  -0.0452   0.0045   1.0000
  13.250   1.5597   0.02643   0.02111  -0.0432   0.0044   1.0000
  13.500   1.5680   0.02751   0.02230  -0.0412   0.0043   1.0000
  13.750   1.5755   0.02869   0.02358  -0.0393   0.0041   1.0000
  14.000   1.5819   0.03001   0.02500  -0.0374   0.0039   1.0000
  14.250   1.5874   0.03146   0.02653  -0.0357   0.0038   1.0000
  14.500   1.5914   0.03309   0.02827  -0.0341   0.0036   1.0000
  14.750   1.5943   0.03490   0.03018  -0.0326   0.0035   1.0000
  15.000   1.5961   0.03690   0.03228  -0.0313   0.0034   1.0000
  15.250   1.5963   0.03916   0.03465  -0.0302   0.0033   1.0000
  15.500   1.5945   0.04173   0.03734  -0.0293   0.0033   1.0000
  15.750   1.5907   0.04467   0.04040  -0.0287   0.0031   1.0000
  16.000   1.5845   0.04805   0.04391  -0.0285   0.0031   1.0000
  16.250   1.5759   0.05194   0.04794  -0.0287   0.0030   1.0000
  16.500   1.5632   0.05670   0.05286  -0.0297   0.0029   1.0000
  16.750   1.5519   0.06165   0.05795  -0.0312   0.0029   1.0000
  17.000   1.5402   0.06714   0.06359  -0.0334   0.0029   1.0000
  17.250   1.5242   0.07385   0.07046  -0.0366   0.0029   1.0000
  17.500   1.5071   0.08122   0.07799  -0.0406   0.0029   1.0000
  17.750   1.4854   0.08989   0.08683  -0.0454   0.0029   1.0000
  18.000   1.4559   0.10038   0.09751  -0.0514   0.0029   1.0000
  18.250   1.4228   0.11195   0.10925  -0.0582   0.0029   1.0000
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