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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 50,000
Max Cl/Cd: 35.92 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2511-il-50000.txt
Download as CSV file: xf-hq2511-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3800   0.10546   0.09871  -0.0249   1.0000   0.2632
  -8.750  -0.3916   0.10421   0.09757  -0.0250   1.0000   0.2752
  -8.500  -0.3894   0.10138   0.09483  -0.0240   1.0000   0.2902
  -8.250  -0.3905   0.09886   0.09240  -0.0228   1.0000   0.3055
  -8.000  -0.3602   0.09373   0.08722  -0.0206   1.0000   0.3259
  -7.750  -0.3596   0.09131   0.08488  -0.0188   1.0000   0.3461
  -7.500  -0.3677   0.08957   0.08327  -0.0169   1.0000   0.3631
  -7.250  -0.3785   0.08809   0.08193  -0.0144   1.0000   0.3788
  -7.000  -0.3565   0.08401   0.07786  -0.0121   1.0000   0.4059
  -6.750  -0.3468   0.08106   0.07496  -0.0093   1.0000   0.4331
  -6.000  -0.5069   0.05613   0.04946  -0.0417   1.0000   0.1303
  -5.750  -0.4961   0.05196   0.04509  -0.0413   1.0000   0.1228
  -5.500  -0.4829   0.04692   0.03907  -0.0426   1.0000   0.1134
  -5.250  -0.4666   0.04338   0.03503  -0.0424   1.0000   0.1136
  -5.000  -0.4487   0.03984   0.03123  -0.0421   1.0000   0.1163
  -4.750  -0.4291   0.03719   0.02831  -0.0416   1.0000   0.1236
  -4.500  -0.4085   0.03481   0.02563  -0.0412   1.0000   0.1373
  -4.250  -0.3854   0.03248   0.02296  -0.0407   1.0000   0.1527
  -4.000  -0.3609   0.03036   0.02050  -0.0401   1.0000   0.1653
  -3.750  -0.3369   0.02872   0.01862  -0.0394   1.0000   0.1783
  -3.500  -0.3139   0.02742   0.01720  -0.0385   1.0000   0.1935
  -3.250  -0.2914   0.02628   0.01602  -0.0374   1.0000   0.2112
  -3.000  -0.2695   0.02521   0.01500  -0.0362   1.0000   0.2355
  -2.750  -0.2466   0.02406   0.01405  -0.0355   1.0000   0.2777
  -2.500  -0.2327   0.02177   0.01411  -0.0318   1.0000   0.5900
  -2.250  -0.2421   0.02211   0.01482  -0.0209   1.0000   0.7704
  -2.000  -0.2453   0.02206   0.01480  -0.0126   1.0000   0.8484
  -1.750  -0.1585   0.02260   0.01489  -0.0195   1.0000   1.0000
  -1.500  -0.1615   0.02210   0.01422  -0.0170   1.0000   1.0000
  -1.250  -0.1502   0.02192   0.01379  -0.0166   1.0000   1.0000
  -1.000  -0.1311   0.02199   0.01357  -0.0173   1.0000   1.0000
  -0.750  -0.1092   0.02222   0.01351  -0.0182   1.0000   1.0000
  -0.500  -0.0864   0.02254   0.01356  -0.0192   1.0000   1.0000
  -0.250  -0.0635   0.02295   0.01373  -0.0201   1.0000   1.0000
   0.000  -0.0410   0.02342   0.01397  -0.0209   1.0000   1.0000
   0.250  -0.0189   0.02395   0.01431  -0.0216   1.0000   1.0000
   0.500   0.0027   0.02454   0.01470  -0.0223   1.0000   1.0000
   0.750   0.0236   0.02518   0.01519  -0.0228   1.0000   1.0000
   1.000   0.0441   0.02588   0.01576  -0.0233   1.0000   1.0000
   1.250   0.0812   0.02709   0.01684  -0.0270   0.9919   1.0000
   1.500   0.1263   0.02852   0.01814  -0.0320   0.9781   1.0000
   1.750   0.1695   0.02987   0.01941  -0.0365   0.9634   1.0000
   2.000   0.2146   0.03120   0.02067  -0.0412   0.9464   1.0000
   2.250   0.2660   0.03253   0.02195  -0.0465   0.9267   1.0000
   2.500   0.3042   0.03343   0.02286  -0.0494   0.9061   1.0000
   2.750   0.3484   0.03441   0.02385  -0.0531   0.8872   1.0000
   3.000   0.3955   0.03535   0.02483  -0.0569   0.8695   1.0000
   3.250   0.4240   0.03613   0.02567  -0.0578   0.8500   1.0000
   3.500   0.4617   0.03685   0.02646  -0.0598   0.8305   1.0000
   3.750   0.5080   0.03736   0.02708  -0.0626   0.8117   1.0000
   4.000   0.5389   0.03790   0.02774  -0.0632   0.7903   1.0000
   4.250   0.5821   0.03806   0.02804  -0.0649   0.7697   1.0000
   4.500   0.6243   0.03805   0.02819  -0.0662   0.7490   1.0000
   4.750   0.6653   0.03777   0.02813  -0.0669   0.7266   1.0000
   5.000   0.7194   0.03657   0.02718  -0.0681   0.7049   1.0000
   5.250   0.7689   0.03494   0.02581  -0.0680   0.6814   1.0000
   5.500   0.8124   0.03334   0.02442  -0.0669   0.6555   1.0000
   5.750   0.8592   0.03131   0.02261  -0.0658   0.6277   1.0000
   6.000   0.9017   0.02954   0.02097  -0.0644   0.5960   1.0000
   6.250   0.9418   0.02808   0.01952  -0.0629   0.5605   1.0000
   6.500   0.9703   0.02769   0.01911  -0.0609   0.5211   1.0000
   6.750   0.9969   0.02786   0.01915  -0.0591   0.4812   1.0000
   7.000   1.0241   0.02851   0.01957  -0.0578   0.4432   1.0000
   7.250   1.0457   0.02974   0.02076  -0.0563   0.4095   1.0000
   7.500   1.0682   0.03105   0.02207  -0.0551   0.3808   1.0000
   7.750   1.0932   0.03231   0.02324  -0.0542   0.3563   1.0000
   8.000   1.1126   0.03399   0.02513  -0.0529   0.3361   1.0000
   8.250   1.1358   0.03558   0.02679  -0.0520   0.3171   1.0000
   8.500   1.1579   0.03721   0.02845  -0.0510   0.2974   1.0000
   8.750   1.1723   0.03792   0.02908  -0.0489   0.2685   1.0000
   9.000   1.1780   0.03830   0.02940  -0.0458   0.2381   1.0000
   9.250   1.1851   0.03926   0.03035  -0.0430   0.2098   1.0000
   9.500   1.1854   0.04089   0.03199  -0.0393   0.1773   1.0000
   9.750   1.1866   0.04301   0.03386  -0.0359   0.1448   1.0000
  10.000   1.1960   0.04620   0.03706  -0.0337   0.1242   1.0000
  10.250   1.2077   0.04933   0.04030  -0.0319   0.1118   1.0000
  10.500   1.2238   0.05226   0.04314  -0.0309   0.1014   1.0000
  10.750   1.2192   0.05585   0.04736  -0.0279   0.0978   1.0000
  11.000   1.2164   0.05965   0.05162  -0.0254   0.0949   1.0000
  11.250   1.2125   0.06331   0.05557  -0.0231   0.0927   1.0000
  11.500   1.2098   0.06707   0.05952  -0.0212   0.0908   1.0000
  11.750   1.2136   0.07161   0.06410  -0.0203   0.0886   1.0000
  12.000   1.1934   0.07575   0.06854  -0.0181   0.0886   1.0000
  12.250   1.1146   0.08255   0.07596  -0.0179   0.0942   1.0000
  12.500   1.0763   0.09010   0.08371  -0.0207   0.0964   1.0000
  12.750   1.0426   0.09858   0.09230  -0.0249   0.0984   1.0000
  13.000   1.0167   0.10737   0.10114  -0.0295   0.1001   1.0000
  13.250   0.9967   0.11630   0.11007  -0.0341   0.1012   1.0000
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