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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 500,000
Max Cl/Cd: 83.72 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2512-il-500000-n5.txt
Download as CSV file: xf-hq2512-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7184   0.06349   0.06087  -0.0582   1.0000   0.0055
 -12.750  -0.7696   0.04868   0.04573  -0.0698   1.0000   0.0054
 -12.500  -0.7872   0.04303   0.03993  -0.0736   1.0000   0.0054
 -12.250  -0.8058   0.03833   0.03502  -0.0758   1.0000   0.0053
 -12.000  -0.8174   0.03527   0.03182  -0.0759   1.0000   0.0054
 -11.750  -0.8307   0.03313   0.02954  -0.0740   1.0000   0.0054
 -11.500  -0.8441   0.03120   0.02745  -0.0705   1.0000   0.0054
 -11.250  -0.8351   0.02957   0.02568  -0.0700   0.9975   0.0056
 -11.000  -0.8145   0.02756   0.02345  -0.0716   0.9895   0.0058
 -10.750  -0.7901   0.02563   0.02129  -0.0736   0.9842   0.0060
 -10.500  -0.7660   0.02396   0.01940  -0.0749   0.9778   0.0062
 -10.250  -0.7387   0.02249   0.01772  -0.0765   0.9725   0.0065
 -10.000  -0.7129   0.02117   0.01622  -0.0775   0.9653   0.0066
  -9.750  -0.6847   0.02009   0.01495  -0.0786   0.9587   0.0069
  -9.500  -0.6596   0.01896   0.01364  -0.0791   0.9499   0.0071
  -9.250  -0.6344   0.01780   0.01235  -0.0796   0.9412   0.0076
  -9.000  -0.6093   0.01707   0.01152  -0.0797   0.9313   0.0080
  -8.750  -0.5842   0.01644   0.01079  -0.0797   0.9222   0.0085
  -8.500  -0.5589   0.01589   0.01013  -0.0795   0.9137   0.0091
  -8.250  -0.5348   0.01531   0.00943  -0.0791   0.9047   0.0096
  -8.000  -0.5104   0.01477   0.00876  -0.0787   0.8966   0.0100
  -7.750  -0.4870   0.01409   0.00796  -0.0782   0.8882   0.0108
  -7.500  -0.4625   0.01358   0.00738  -0.0778   0.8805   0.0116
  -7.250  -0.4375   0.01316   0.00687  -0.0774   0.8730   0.0126
  -7.000  -0.4121   0.01277   0.00639  -0.0771   0.8659   0.0138
  -6.750  -0.3869   0.01235   0.00594  -0.0768   0.8589   0.0163
  -6.500  -0.3610   0.01203   0.00558  -0.0765   0.8523   0.0192
  -6.250  -0.3349   0.01172   0.00525  -0.0763   0.8456   0.0235
  -6.000  -0.3082   0.01152   0.00497  -0.0761   0.8395   0.0265
  -5.750  -0.2820   0.01122   0.00465  -0.0759   0.8327   0.0303
  -5.500  -0.2553   0.01101   0.00439  -0.0758   0.8267   0.0335
  -5.250  -0.2282   0.01084   0.00415  -0.0756   0.8201   0.0360
  -5.000  -0.2017   0.01058   0.00387  -0.0755   0.8141   0.0409
  -4.750  -0.1745   0.01039   0.00367  -0.0754   0.8077   0.0457
  -4.500  -0.1475   0.01018   0.00342  -0.0753   0.8015   0.0505
  -4.250  -0.1205   0.00997   0.00319  -0.0752   0.7954   0.0561
  -4.000  -0.0932   0.00980   0.00297  -0.0751   0.7891   0.0625
  -3.750  -0.0660   0.00961   0.00277  -0.0750   0.7832   0.0725
  -3.500  -0.0387   0.00941   0.00259  -0.0749   0.7767   0.0858
  -3.000   0.0154   0.00895   0.00225  -0.0748   0.7640   0.1384
  -2.750   0.0421   0.00867   0.00210  -0.0748   0.7575   0.1873
  -2.500   0.0690   0.00839   0.00196  -0.0747   0.7505   0.2372
  -2.250   0.0954   0.00806   0.00181  -0.0747   0.7434   0.3032
  -2.000   0.1209   0.00754   0.00169  -0.0746   0.7363   0.4268
  -1.750   0.1475   0.00731   0.00165  -0.0744   0.7296   0.4978
  -1.500   0.1749   0.00721   0.00164  -0.0743   0.7233   0.5378
  -1.250   0.2024   0.00716   0.00163  -0.0742   0.7163   0.5704
  -1.000   0.2296   0.00712   0.00166  -0.0740   0.7084   0.6067
  -0.750   0.2570   0.00713   0.00166  -0.0737   0.6992   0.6276
  -0.500   0.2847   0.00715   0.00165  -0.0737   0.6893   0.6398
  -0.250   0.3124   0.00717   0.00165  -0.0735   0.6795   0.6504
   0.000   0.3397   0.00721   0.00165  -0.0733   0.6686   0.6607
   0.250   0.3672   0.00724   0.00167  -0.0732   0.6577   0.6716
   0.500   0.3950   0.00728   0.00169  -0.0731   0.6481   0.6805
   0.750   0.4225   0.00732   0.00171  -0.0730   0.6391   0.6868
   1.000   0.4501   0.00737   0.00174  -0.0729   0.6284   0.6933
   1.250   0.4777   0.00743   0.00177  -0.0728   0.6171   0.6994
   1.500   0.5048   0.00749   0.00181  -0.0727   0.6038   0.7058
   1.750   0.5320   0.00757   0.00186  -0.0725   0.5895   0.7125
   2.000   0.5587   0.00766   0.00192  -0.0722   0.5739   0.7191
   2.500   0.6114   0.00789   0.00206  -0.0716   0.5369   0.7330
   2.750   0.6371   0.00806   0.00217  -0.0713   0.5136   0.7404
   3.000   0.6620   0.00827   0.00229  -0.0707   0.4854   0.7476
   3.500   0.7104   0.00881   0.00262  -0.0695   0.4225   0.7632
   3.750   0.7347   0.00909   0.00281  -0.0689   0.3949   0.7713
   4.000   0.7586   0.00937   0.00301  -0.0683   0.3659   0.7800
   4.250   0.7822   0.00969   0.00323  -0.0676   0.3349   0.7890
   4.750   0.8294   0.01027   0.00369  -0.0663   0.2885   0.8101
   5.000   0.8526   0.01055   0.00394  -0.0655   0.2693   0.8223
   5.250   0.8755   0.01083   0.00419  -0.0647   0.2520   0.8372
   5.500   0.8983   0.01105   0.00445  -0.0638   0.2370   0.8558
   5.750   0.9204   0.01120   0.00468  -0.0627   0.2255   0.8864
   6.000   0.9544   0.01140   0.00495  -0.0643   0.2107   1.0000
   6.250   0.9783   0.01172   0.00522  -0.0638   0.1971   1.0000
   6.500   1.0010   0.01211   0.00554  -0.0631   0.1783   1.0000
   6.750   1.0236   0.01250   0.00585  -0.0624   0.1612   1.0000
   7.000   1.0459   0.01289   0.00619  -0.0616   0.1469   1.0000
   7.250   1.0676   0.01332   0.00655  -0.0608   0.1317   1.0000
   7.500   1.0875   0.01386   0.00697  -0.0597   0.1125   1.0000
   7.750   1.1075   0.01437   0.00742  -0.0586   0.0962   1.0000
   8.000   1.1272   0.01489   0.00787  -0.0574   0.0822   1.0000
   8.250   1.1462   0.01542   0.00834  -0.0562   0.0697   1.0000
   8.500   1.1645   0.01598   0.00885  -0.0549   0.0585   1.0000
   8.750   1.1817   0.01657   0.00939  -0.0534   0.0479   1.0000
   9.000   1.1924   0.01743   0.01012  -0.0508   0.0295   1.0000
   9.250   1.1980   0.01860   0.01114  -0.0476   0.0099   1.0000
   9.500   1.2109   0.01933   0.01191  -0.0455   0.0068   1.0000
   9.750   1.2238   0.02008   0.01270  -0.0435   0.0054   1.0000
  10.000   1.2378   0.02078   0.01346  -0.0417   0.0049   1.0000
  10.250   1.2509   0.02155   0.01429  -0.0399   0.0044   1.0000
  10.500   1.2629   0.02240   0.01521  -0.0381   0.0041   1.0000
  10.750   1.2737   0.02336   0.01627  -0.0362   0.0038   1.0000
  11.000   1.2846   0.02434   0.01734  -0.0344   0.0037   1.0000
  11.250   1.2958   0.02533   0.01841  -0.0328   0.0036   1.0000
  11.500   1.3062   0.02640   0.01959  -0.0312   0.0035   1.0000
  11.750   1.3152   0.02760   0.02088  -0.0296   0.0034   1.0000
  12.000   1.3233   0.02891   0.02229  -0.0281   0.0033   1.0000
  12.250   1.3301   0.03036   0.02385  -0.0266   0.0032   1.0000
  12.500   1.3363   0.03192   0.02550  -0.0252   0.0032   1.0000
  12.750   1.3408   0.03368   0.02737  -0.0239   0.0031   1.0000
  13.000   1.3447   0.03554   0.02934  -0.0228   0.0031   1.0000
  13.250   1.3466   0.03767   0.03158  -0.0217   0.0029   1.0000
  13.500   1.3478   0.03996   0.03398  -0.0208   0.0029   1.0000
  13.750   1.3476   0.04248   0.03662  -0.0202   0.0028   1.0000
  14.000   1.3466   0.04519   0.03944  -0.0197   0.0028   1.0000
  14.250   1.3440   0.04821   0.04259  -0.0195   0.0027   1.0000
  14.500   1.3401   0.05152   0.04603  -0.0196   0.0027   1.0000
  14.750   1.3350   0.05517   0.04982  -0.0200   0.0027   1.0000
  15.000   1.3286   0.05920   0.05398  -0.0208   0.0027   1.0000
  15.250   1.3217   0.06350   0.05841  -0.0219   0.0026   1.0000
  15.500   1.3094   0.06888   0.06393  -0.0236   0.0025   1.0000
  15.750   1.3025   0.07367   0.06886  -0.0254   0.0026   1.0000
  16.000   1.2919   0.07928   0.07460  -0.0277   0.0026   1.0000
  16.250   1.2783   0.08566   0.08112  -0.0306   0.0025   1.0000
  16.500   1.2656   0.09212   0.08772  -0.0336   0.0025   1.0000
  16.750   1.2547   0.09843   0.09417  -0.0367   0.0025   1.0000
  17.000   1.2380   0.10602   0.10190  -0.0405   0.0025   1.0000
  17.250   1.2275   0.11256   0.10857  -0.0439   0.0025   1.0000
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