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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 200,000
Max Cl/Cd: 73.75 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3013-il-200000-n5.txt
Download as CSV file: xf-hq3013-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/13 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6089   0.04937   0.04552  -0.0757   1.0000   0.0140
 -10.500  -0.6452   0.04436   0.04029  -0.0770   0.9947   0.0139
 -10.250  -0.6430   0.03893   0.03440  -0.0826   0.9819   0.0140
 -10.000  -0.6305   0.03515   0.03022  -0.0856   0.9730   0.0143
  -9.750  -0.6138   0.03208   0.02675  -0.0874   0.9652   0.0147
  -9.500  -0.5924   0.02945   0.02376  -0.0890   0.9588   0.0152
  -9.250  -0.5713   0.02728   0.02123  -0.0898   0.9514   0.0158
  -9.000  -0.5470   0.02536   0.01899  -0.0906   0.9451   0.0164
  -8.750  -0.5221   0.02383   0.01725  -0.0913   0.9392   0.0171
  -8.500  -0.4967   0.02294   0.01628  -0.0917   0.9322   0.0179
  -8.250  -0.4670   0.02213   0.01535  -0.0928   0.9276   0.0194
  -8.000  -0.4437   0.02116   0.01419  -0.0925   0.9198   0.0208
  -7.750  -0.4170   0.02010   0.01300  -0.0929   0.9144   0.0223
  -7.500  -0.3918   0.01939   0.01222  -0.0928   0.9076   0.0241
  -7.250  -0.3660   0.01862   0.01129  -0.0928   0.9014   0.0269
  -7.000  -0.3398   0.01791   0.01054  -0.0928   0.8958   0.0300
  -6.750  -0.3149   0.01744   0.00997  -0.0925   0.8888   0.0338
  -6.500  -0.2878   0.01694   0.00941  -0.0926   0.8836   0.0381
  -6.250  -0.2624   0.01664   0.00902  -0.0923   0.8768   0.0427
  -6.000  -0.2363   0.01624   0.00859  -0.0922   0.8710   0.0478
  -5.750  -0.2092   0.01599   0.00826  -0.0922   0.8657   0.0534
  -5.500  -0.1844   0.01554   0.00775  -0.0918   0.8592   0.0579
  -5.250  -0.1581   0.01510   0.00726  -0.0917   0.8542   0.0624
  -5.000  -0.1327   0.01474   0.00682  -0.0913   0.8482   0.0665
  -4.750  -0.1071   0.01433   0.00637  -0.0910   0.8423   0.0713
  -4.250  -0.0549   0.01366   0.00564  -0.0906   0.8313   0.0877
  -4.000  -0.0284   0.01335   0.00531  -0.0904   0.8259   0.0997
  -3.750  -0.0018   0.01302   0.00501  -0.0903   0.8210   0.1194
  -3.500   0.0234   0.01265   0.00476  -0.0901   0.8147   0.1557
  -3.250   0.0491   0.01214   0.00450  -0.0900   0.8096   0.2266
  -3.000   0.0730   0.01149   0.00426  -0.0898   0.8040   0.3344
  -2.750   0.0967   0.01104   0.00429  -0.0892   0.7979   0.4765
  -2.500   0.1240   0.01095   0.00426  -0.0889   0.7932   0.5248
  -2.250   0.1503   0.01094   0.00426  -0.0884   0.7866   0.5549
  -2.000   0.1778   0.01093   0.00421  -0.0882   0.7808   0.5785
  -1.750   0.2047   0.01093   0.00422  -0.0878   0.7748   0.6017
  -1.500   0.2311   0.01096   0.00426  -0.0872   0.7680   0.6280
  -1.250   0.2587   0.01097   0.00423  -0.0869   0.7627   0.6456
  -1.000   0.2854   0.01099   0.00423  -0.0866   0.7556   0.6568
  -0.750   0.3129   0.01099   0.00421  -0.0863   0.7499   0.6684
  -0.500   0.3398   0.01101   0.00423  -0.0860   0.7438   0.6792
  -0.250   0.3673   0.01102   0.00421  -0.0859   0.7373   0.6878
   0.000   0.3952   0.01102   0.00417  -0.0858   0.7318   0.6936
   0.250   0.4221   0.01104   0.00418  -0.0856   0.7241   0.7007
   0.500   0.4495   0.01102   0.00413  -0.0853   0.7163   0.7071
   1.000   0.5027   0.01100   0.00409  -0.0846   0.6951   0.7211
   1.250   0.5300   0.01102   0.00407  -0.0843   0.6869   0.7288
   1.500   0.5565   0.01104   0.00411  -0.0840   0.6781   0.7367
   1.750   0.5833   0.01107   0.00414  -0.0837   0.6694   0.7453
   2.000   0.6098   0.01109   0.00417  -0.0833   0.6601   0.7534
   2.250   0.6360   0.01114   0.00422  -0.0829   0.6490   0.7630
   2.500   0.6615   0.01117   0.00428  -0.0823   0.6367   0.7723
   2.750   0.6871   0.01122   0.00432  -0.0818   0.6231   0.7826
   3.000   0.7125   0.01128   0.00438  -0.0812   0.6088   0.7938
   3.250   0.7372   0.01134   0.00446  -0.0805   0.5941   0.8052
   3.500   0.7615   0.01141   0.00455  -0.0797   0.5785   0.8180
   3.750   0.7854   0.01149   0.00463  -0.0788   0.5614   0.8325
   4.000   0.8091   0.01160   0.00474  -0.0779   0.5428   0.8489
   4.500   0.8558   0.01185   0.00498  -0.0760   0.4988   0.8989
   4.750   0.8887   0.01205   0.00515  -0.0772   0.4711   1.0000
   5.000   0.9108   0.01241   0.00539  -0.0764   0.4465   1.0000
   5.250   0.9322   0.01280   0.00566  -0.0754   0.4222   1.0000
   5.500   0.9535   0.01319   0.00595  -0.0744   0.3990   1.0000
   5.750   0.9737   0.01364   0.00630  -0.0732   0.3757   1.0000
   6.000   0.9940   0.01407   0.00665  -0.0721   0.3525   1.0000
   6.250   1.0134   0.01454   0.00703  -0.0708   0.3311   1.0000
   6.500   1.0326   0.01502   0.00743  -0.0695   0.3110   1.0000
   6.750   1.0511   0.01552   0.00787  -0.0682   0.2928   1.0000
   7.000   1.0695   0.01602   0.00832  -0.0668   0.2769   1.0000
   7.250   1.0875   0.01653   0.00879  -0.0654   0.2623   1.0000
   7.500   1.1047   0.01705   0.00928  -0.0638   0.2477   1.0000
   7.750   1.1207   0.01757   0.00978  -0.0620   0.2343   1.0000
   8.000   1.1361   0.01810   0.01030  -0.0602   0.2213   1.0000
   8.250   1.1510   0.01868   0.01085  -0.0584   0.2091   1.0000
   8.500   1.1653   0.01930   0.01145  -0.0565   0.1971   1.0000
   8.750   1.1801   0.01992   0.01207  -0.0548   0.1857   1.0000
   9.000   1.1946   0.02058   0.01274  -0.0531   0.1746   1.0000
   9.250   1.2086   0.02128   0.01345  -0.0514   0.1652   1.0000
   9.500   1.2214   0.02206   0.01421  -0.0496   0.1558   1.0000
   9.750   1.2357   0.02279   0.01498  -0.0481   0.1456   1.0000
  10.000   1.2485   0.02361   0.01582  -0.0465   0.1359   1.0000
  10.250   1.2601   0.02453   0.01673  -0.0449   0.1251   1.0000
  10.500   1.2711   0.02552   0.01772  -0.0433   0.1148   1.0000
  10.750   1.2830   0.02649   0.01872  -0.0419   0.1048   1.0000
  11.000   1.2938   0.02757   0.01982  -0.0404   0.0963   1.0000
  11.250   1.3028   0.02879   0.02103  -0.0389   0.0866   1.0000
  11.500   1.3120   0.03005   0.02229  -0.0375   0.0775   1.0000
  11.750   1.3212   0.03134   0.02362  -0.0362   0.0702   1.0000
  12.000   1.3284   0.03282   0.02511  -0.0349   0.0639   1.0000
  12.250   1.3368   0.03424   0.02661  -0.0337   0.0579   1.0000
  12.500   1.3425   0.03593   0.02832  -0.0325   0.0532   1.0000
  12.750   1.3505   0.03746   0.02996  -0.0315   0.0493   1.0000
  13.000   1.3564   0.03922   0.03179  -0.0305   0.0457   1.0000
  13.250   1.3607   0.04118   0.03381  -0.0296   0.0427   1.0000
  13.500   1.3665   0.04303   0.03577  -0.0289   0.0395   1.0000
  13.750   1.3700   0.04518   0.03800  -0.0282   0.0362   1.0000
  14.000   1.3720   0.04754   0.04044  -0.0276   0.0336   1.0000
  14.250   1.3757   0.04980   0.04282  -0.0272   0.0312   1.0000
  14.500   1.3760   0.05250   0.04560  -0.0269   0.0279   1.0000
  14.750   1.3761   0.05535   0.04856  -0.0268   0.0248   1.0000
  15.000   1.3744   0.05850   0.05179  -0.0270   0.0213   1.0000
  15.250   1.3723   0.06182   0.05523  -0.0273   0.0191   1.0000
  15.500   1.3694   0.06538   0.05891  -0.0278   0.0171   1.0000
  15.750   1.3628   0.06959   0.06321  -0.0287   0.0146   1.0000
  16.000   1.3565   0.07391   0.06766  -0.0298   0.0129   1.0000
  16.250   1.3478   0.07877   0.07262  -0.0313   0.0116   1.0000
  16.500   1.3403   0.08365   0.07767  -0.0330   0.0109   1.0000
  16.750   1.3299   0.08914   0.08330  -0.0351   0.0099   1.0000
  17.000   1.3189   0.09492   0.08924  -0.0376   0.0094   1.0000
  17.250   1.3063   0.10119   0.09566  -0.0404   0.0090   1.0000
  17.750   1.2785   0.11472   0.10950  -0.0470   0.0086   1.0000
  18.000   1.2648   0.12172   0.11667  -0.0507   0.0085   1.0000
  18.250   1.2497   0.12919   0.12431  -0.0548   0.0084   1.0000
  18.500   1.2353   0.13662   0.13188  -0.0589   0.0084   1.0000
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