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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 50,000
Max Cl/Cd: 36.99 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2010-il-50000-n5.txt
Download as CSV file: xf-hq2010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4625   0.12338   0.11607  -0.0204   1.0000   0.0534
 -10.750  -0.4585   0.11914   0.11186  -0.0216   1.0000   0.0508
 -10.500  -0.4571   0.11480   0.10757  -0.0235   1.0000   0.0485
 -10.000  -0.4657   0.10413   0.09706  -0.0309   1.0000   0.0433
  -9.750  -0.4633   0.10002   0.09300  -0.0321   1.0000   0.0429
  -9.500  -0.4623   0.09581   0.08885  -0.0336   1.0000   0.0424
  -9.250  -0.4634   0.09136   0.08447  -0.0356   1.0000   0.0421
  -9.000  -0.4661   0.08668   0.07988  -0.0380   1.0000   0.0419
  -8.750  -0.4704   0.08177   0.07505  -0.0409   1.0000   0.0416
  -8.500  -0.4781   0.07685   0.07019  -0.0441   1.0000   0.0412
  -8.250  -0.4893   0.07240   0.06581  -0.0463   1.0000   0.0408
  -8.000  -0.4991   0.06802   0.06141  -0.0479   1.0000   0.0406
  -7.750  -0.5071   0.06391   0.05723  -0.0487   1.0000   0.0404
  -7.500  -0.5138   0.05987   0.05305  -0.0489   1.0000   0.0405
  -7.250  -0.5175   0.05600   0.04897  -0.0486   1.0000   0.0409
  -7.000  -0.5181   0.05225   0.04492  -0.0478   1.0000   0.0417
  -6.750  -0.5155   0.04863   0.04090  -0.0468   1.0000   0.0426
  -6.500  -0.5094   0.04523   0.03700  -0.0455   1.0000   0.0434
  -6.250  -0.5002   0.04195   0.03331  -0.0441   1.0000   0.0441
  -6.000  -0.4883   0.03903   0.03014  -0.0428   1.0000   0.0451
  -5.750  -0.4740   0.03654   0.02730  -0.0415   1.0000   0.0467
  -5.500  -0.4576   0.03434   0.02480  -0.0402   1.0000   0.0489
  -5.250  -0.4397   0.03244   0.02250  -0.0389   1.0000   0.0537
  -5.000  -0.4206   0.03048   0.02020  -0.0376   1.0000   0.0584
  -4.750  -0.4013   0.02888   0.01848  -0.0363   1.0000   0.0633
  -4.500  -0.3815   0.02752   0.01690  -0.0350   1.0000   0.0724
  -4.250  -0.3617   0.02630   0.01553  -0.0335   1.0000   0.0814
  -4.000  -0.3426   0.02526   0.01443  -0.0322   1.0000   0.0951
  -3.750  -0.3231   0.02423   0.01329  -0.0309   1.0000   0.1085
  -3.500  -0.3027   0.02330   0.01240  -0.0301   1.0000   0.1298
  -3.250  -0.2819   0.02233   0.01151  -0.0295   1.0000   0.1597
  -3.000  -0.2510   0.02077   0.01061  -0.0315   0.9955   0.2690
  -2.750  -0.2275   0.01960   0.01089  -0.0306   0.9889   0.5633
  -2.500  -0.2021   0.01975   0.01116  -0.0291   0.9811   0.6798
  -2.250  -0.1783   0.01994   0.01132  -0.0270   0.9731   0.7570
  -2.000  -0.1582   0.01999   0.01137  -0.0241   0.9647   0.8200
  -1.750  -0.1284   0.02001   0.01132  -0.0231   0.9584   0.8761
  -1.500  -0.0808   0.02004   0.01117  -0.0262   0.9536   0.9283
  -1.250  -0.0207   0.02010   0.01092  -0.0329   0.9495   0.9638
  -1.000   0.0344   0.02015   0.01070  -0.0392   0.9446   0.9913
  -0.750   0.0633   0.02020   0.01054  -0.0409   0.9349   1.0000
  -0.500   0.0934   0.02031   0.01047  -0.0426   0.9261   1.0000
  -0.250   0.1265   0.02047   0.01046  -0.0446   0.9178   1.0000
   0.000   0.1553   0.02066   0.01049  -0.0458   0.9086   1.0000
   0.250   0.1946   0.02085   0.01056  -0.0487   0.9021   1.0000
   0.500   0.2241   0.02105   0.01066  -0.0496   0.8914   1.0000
   0.750   0.2575   0.02124   0.01076  -0.0511   0.8812   1.0000
   1.000   0.2953   0.02137   0.01084  -0.0532   0.8724   1.0000
   1.250   0.3264   0.02157   0.01099  -0.0541   0.8619   1.0000
   1.500   0.3553   0.02180   0.01121  -0.0546   0.8512   1.0000
   1.750   0.3869   0.02197   0.01139  -0.0554   0.8404   1.0000
   2.000   0.4200   0.02200   0.01143  -0.0560   0.8272   1.0000
   2.250   0.4518   0.02193   0.01138  -0.0562   0.8114   1.0000
   2.500   0.4832   0.02181   0.01132  -0.0561   0.7950   1.0000
   2.750   0.5135   0.02173   0.01129  -0.0559   0.7795   1.0000
   3.000   0.5422   0.02173   0.01135  -0.0556   0.7650   1.0000
   3.250   0.5707   0.02171   0.01141  -0.0552   0.7499   1.0000
   3.500   0.5993   0.02166   0.01149  -0.0546   0.7343   1.0000
   3.750   0.6243   0.02171   0.01164  -0.0537   0.7159   1.0000
   4.000   0.6505   0.02170   0.01174  -0.0527   0.6967   1.0000
   4.250   0.6786   0.02160   0.01174  -0.0519   0.6769   1.0000
   4.500   0.7032   0.02163   0.01193  -0.0507   0.6528   1.0000
   4.750   0.7282   0.02164   0.01205  -0.0494   0.6262   1.0000
   5.000   0.7534   0.02165   0.01215  -0.0481   0.5961   1.0000
   5.250   0.7777   0.02175   0.01229  -0.0467   0.5613   1.0000
   5.500   0.8018   0.02191   0.01247  -0.0452   0.5231   1.0000
   5.750   0.8236   0.02228   0.01277  -0.0436   0.4805   1.0000
   6.000   0.8438   0.02281   0.01318  -0.0420   0.4365   1.0000
   6.250   0.8627   0.02353   0.01369  -0.0403   0.3954   1.0000
   6.500   0.8802   0.02440   0.01442  -0.0386   0.3557   1.0000
   6.750   0.8967   0.02533   0.01526  -0.0371   0.3179   1.0000
   7.000   0.9123   0.02636   0.01622  -0.0355   0.2837   1.0000
   7.250   0.9275   0.02747   0.01729  -0.0339   0.2493   1.0000
   7.500   0.9417   0.02865   0.01843  -0.0323   0.2164   1.0000
   7.750   0.9556   0.02991   0.01966  -0.0308   0.1846   1.0000
   8.000   0.9697   0.03132   0.02101  -0.0292   0.1591   1.0000
   8.250   0.9842   0.03280   0.02248  -0.0278   0.1370   1.0000
   8.500   0.9979   0.03435   0.02396  -0.0264   0.1205   1.0000
   8.750   1.0156   0.03602   0.02580  -0.0253   0.1088   1.0000
   9.000   1.0354   0.03783   0.02776  -0.0243   0.0995   1.0000
   9.250   1.0518   0.03964   0.02964  -0.0232   0.0908   1.0000
   9.500   1.0675   0.04150   0.03168  -0.0221   0.0827   1.0000
   9.750   1.0886   0.04402   0.03446  -0.0213   0.0770   1.0000
  10.000   1.1019   0.04636   0.03705  -0.0200   0.0707   1.0000
  10.250   1.1097   0.04891   0.03984  -0.0185   0.0644   1.0000
  10.500   1.1160   0.05199   0.04330  -0.0167   0.0596   1.0000
  10.750   1.1174   0.05443   0.04572  -0.0150   0.0545   1.0000
  11.000   1.1065   0.05729   0.04904  -0.0126   0.0504   1.0000
  11.250   1.0993   0.05962   0.05149  -0.0113   0.0461   1.0000
  11.500   1.0931   0.06257   0.05445  -0.0105   0.0428   1.0000
  11.750   1.0785   0.06692   0.05922  -0.0102   0.0412   1.0000
  12.000   1.0624   0.07178   0.06441  -0.0107   0.0400   1.0000
  12.250   1.0458   0.07720   0.07010  -0.0122   0.0396   1.0000
  12.500   1.0259   0.08347   0.07661  -0.0148   0.0394   1.0000
  12.750   1.0051   0.09065   0.08399  -0.0184   0.0401   1.0000
  13.000   0.9837   0.09874   0.09223  -0.0231   0.0411   1.0000
  13.250   0.9633   0.10748   0.10109  -0.0283   0.0420   1.0000
  13.500   0.9467   0.11612   0.10979  -0.0333   0.0429   1.0000
  13.750   0.9300   0.12550   0.11919  -0.0388   0.0434   1.0000
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