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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 200,000
Max Cl/Cd: 83.55 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3010-il-200000.txt
Download as CSV file: xf-hq3010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3847   0.08989   0.08664  -0.0463   1.0000   0.0386
  -8.250  -0.4024   0.08780   0.08465  -0.0448   1.0000   0.0386
  -8.000  -0.4235   0.08607   0.08301  -0.0428   1.0000   0.0386
  -7.750  -0.4409   0.08363   0.08058  -0.0425   1.0000   0.0387
  -7.500  -0.4545   0.08115   0.07809  -0.0416   1.0000   0.0387
  -7.250  -0.4680   0.07553   0.07261  -0.0392   1.0000   0.0396
  -7.000  -0.4511   0.07201   0.06910  -0.0404   0.9970   0.0407
  -6.750  -0.4292   0.06755   0.06460  -0.0455   0.9927   0.0423
  -6.500  -0.4063   0.06210   0.05903  -0.0528   0.9867   0.0441
  -6.250  -0.3768   0.05589   0.05258  -0.0617   0.9819   0.0474
  -6.000  -0.3496   0.04911   0.04499  -0.0705   0.9729   0.0518
  -5.750  -0.3233   0.04426   0.04024  -0.0735   0.9702   0.0538
  -5.500  -0.2981   0.04166   0.03757  -0.0753   0.9649   0.0580
  -5.250  -0.2679   0.03769   0.03315  -0.0789   0.9595   0.0675
  -5.000  -0.2270   0.02939   0.02378  -0.0806   0.9567   0.0370
  -4.750  -0.1958   0.02506   0.01890  -0.0820   0.9529   0.0332
  -4.500  -0.1655   0.02206   0.01534  -0.0822   0.9477   0.0318
  -4.250  -0.1290   0.02006   0.01302  -0.0836   0.9447   0.0329
  -4.000  -0.0899   0.01871   0.01145  -0.0856   0.9425   0.0365
  -3.750  -0.0590   0.01738   0.01005  -0.0862   0.9378   0.0424
  -3.500  -0.0267   0.01628   0.00888  -0.0869   0.9330   0.0527
  -3.250   0.0115   0.01541   0.00804  -0.0892   0.9301   0.0764
  -3.000   0.0504   0.01468   0.00738  -0.0916   0.9277   0.1006
  -2.750   0.0759   0.01411   0.00689  -0.0914   0.9204   0.1266
  -2.500   0.1038   0.01210   0.00652  -0.0925   0.9163   0.5252
  -2.250   0.1379   0.01190   0.00652  -0.0931   0.9134   0.6412
  -2.000   0.1604   0.01197   0.00661  -0.0916   0.9050   0.6840
  -1.750   0.1929   0.01190   0.00654  -0.0918   0.9009   0.7201
  -1.500   0.2178   0.01193   0.00655  -0.0907   0.8935   0.7471
  -1.250   0.2461   0.01185   0.00648  -0.0900   0.8880   0.7754
  -1.000   0.2680   0.01182   0.00651  -0.0879   0.8809   0.8085
  -0.750   0.2917   0.01168   0.00640  -0.0862   0.8743   0.8353
  -0.500   0.3174   0.01156   0.00625  -0.0854   0.8678   0.8515
  -0.250   0.3436   0.01142   0.00609  -0.0848   0.8608   0.8650
   0.000   0.3704   0.01127   0.00593  -0.0842   0.8547   0.8798
   0.250   0.3957   0.01111   0.00577  -0.0833   0.8468   0.8970
   0.500   0.4235   0.01090   0.00556  -0.0828   0.8384   0.9164
   0.750   0.4590   0.01060   0.00524  -0.0838   0.8306   0.9409
   1.000   0.5021   0.01044   0.00508  -0.0869   0.8214   0.9748
   1.250   0.5385   0.01032   0.00490  -0.0888   0.8142   1.0000
   1.500   0.5660   0.01032   0.00484  -0.0889   0.8043   1.0000
   1.750   0.5939   0.01031   0.00478  -0.0890   0.7941   1.0000
   2.000   0.6223   0.01026   0.00469  -0.0890   0.7838   1.0000
   2.250   0.6507   0.01020   0.00456  -0.0888   0.7727   1.0000
   2.500   0.6781   0.01018   0.00450  -0.0885   0.7603   1.0000
   2.750   0.7050   0.01020   0.00448  -0.0882   0.7472   1.0000
   3.000   0.7317   0.01023   0.00451  -0.0878   0.7336   1.0000
   3.250   0.7585   0.01026   0.00452  -0.0873   0.7192   1.0000
   3.500   0.7850   0.01031   0.00454  -0.0869   0.7036   1.0000
   3.750   0.8105   0.01038   0.00461  -0.0862   0.6850   1.0000
   4.000   0.8363   0.01047   0.00470  -0.0856   0.6655   1.0000
   4.250   0.8615   0.01058   0.00478  -0.0849   0.6434   1.0000
   4.500   0.8863   0.01073   0.00488  -0.0841   0.6185   1.0000
   4.750   0.9102   0.01092   0.00502  -0.0832   0.5888   1.0000
   5.000   0.9332   0.01117   0.00520  -0.0822   0.5537   1.0000
   5.250   0.9551   0.01154   0.00542  -0.0809   0.5133   1.0000
   5.500   0.9755   0.01203   0.00572  -0.0796   0.4695   1.0000
   5.750   0.9950   0.01262   0.00611  -0.0781   0.4255   1.0000
   6.000   1.0141   0.01326   0.00656  -0.0767   0.3835   1.0000
   6.250   1.0332   0.01392   0.00708  -0.0753   0.3440   1.0000
   6.500   1.0519   0.01461   0.00760  -0.0739   0.3091   1.0000
   6.750   1.0711   0.01528   0.00816  -0.0727   0.2790   1.0000
   7.000   1.0903   0.01596   0.00875  -0.0714   0.2529   1.0000
   7.250   1.1096   0.01661   0.00934  -0.0702   0.2290   1.0000
   7.500   1.1290   0.01724   0.00994  -0.0691   0.2057   1.0000
   7.750   1.1473   0.01792   0.01058  -0.0678   0.1808   1.0000
   8.000   1.1647   0.01864   0.01121  -0.0664   0.1540   1.0000
   8.250   1.1816   0.01942   0.01190  -0.0650   0.1294   1.0000
   8.500   1.1975   0.02029   0.01269  -0.0635   0.1071   1.0000
   8.750   1.2128   0.02120   0.01355  -0.0618   0.0872   1.0000
   9.000   1.2263   0.02216   0.01445  -0.0599   0.0714   1.0000
   9.250   1.2383   0.02315   0.01545  -0.0577   0.0601   1.0000
   9.500   1.2487   0.02426   0.01656  -0.0554   0.0479   1.0000
   9.750   1.2520   0.02596   0.01823  -0.0523   0.0337   1.0000
  10.000   1.2540   0.02783   0.02013  -0.0491   0.0235   1.0000
  10.250   1.2603   0.02933   0.02175  -0.0467   0.0199   1.0000
  10.500   1.2612   0.03129   0.02379  -0.0439   0.0179   1.0000
  10.750   1.2571   0.03389   0.02649  -0.0410   0.0169   1.0000
  11.000   1.2634   0.03570   0.02847  -0.0391   0.0161   1.0000
  11.250   1.2683   0.03781   0.03074  -0.0372   0.0155   1.0000
  11.500   1.2731   0.04005   0.03315  -0.0355   0.0149   1.0000
  11.750   1.2775   0.04248   0.03575  -0.0339   0.0143   1.0000
  12.000   1.2815   0.04505   0.03851  -0.0325   0.0140   1.0000
  12.250   1.2842   0.04784   0.04149  -0.0311   0.0137   1.0000
  12.500   1.2851   0.05091   0.04478  -0.0300   0.0135   1.0000
  12.750   1.2834   0.05430   0.04841  -0.0290   0.0134   1.0000
  13.000   1.2786   0.05804   0.05240  -0.0283   0.0133   1.0000
  13.250   1.2708   0.06224   0.05687  -0.0281   0.0133   1.0000
  13.500   1.2600   0.06689   0.06178  -0.0283   0.0133   1.0000
  13.750   1.2466   0.07207   0.06723  -0.0292   0.0134   1.0000
  14.000   1.2304   0.07786   0.07328  -0.0308   0.0135   1.0000
  14.250   1.2119   0.08439   0.08006  -0.0333   0.0136   1.0000
  14.500   1.1925   0.09158   0.08749  -0.0368   0.0138   1.0000
  14.750   1.1717   0.09964   0.09579  -0.0413   0.0140   1.0000
  15.000   1.1498   0.10861   0.10497  -0.0468   0.0141   1.0000
  15.250   1.1275   0.11844   0.11500  -0.0532   0.0143   1.0000
  15.500   1.1042   0.12941   0.12614  -0.0605   0.0146   1.0000
  15.750   1.0778   0.14219   0.13907  -0.0690   0.0149   1.0000
  16.000   1.0470   0.15765   0.15462  -0.0787   0.0155   1.0000
  16.250   1.0210   0.17272   0.16968  -0.0872   0.0163   1.0000
  16.500   1.0094   0.18282   0.17974  -0.0923   0.0169   1.0000
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