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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.97 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3010-il-1000000.txt
Download as CSV file: xf-hq3010-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3822   0.11127   0.10960  -0.0323   1.0000   0.0087
 -10.500  -0.3786   0.10766   0.10600  -0.0336   1.0000   0.0088
 -10.250  -0.3761   0.10380   0.10214  -0.0349   1.0000   0.0088
  -6.750  -0.3071   0.01845   0.01473  -0.0945   0.9165   0.0073
  -6.500  -0.2875   0.01515   0.01087  -0.0936   0.9097   0.0072
  -6.250  -0.2633   0.01385   0.00935  -0.0931   0.9035   0.0075
  -6.000  -0.2378   0.01300   0.00833  -0.0927   0.8981   0.0080
  -5.750  -0.2120   0.01223   0.00743  -0.0924   0.8923   0.0084
  -5.500  -0.1859   0.01162   0.00669  -0.0921   0.8869   0.0086
  -5.250  -0.1593   0.01114   0.00611  -0.0919   0.8815   0.0088
  -5.000  -0.1345   0.01000   0.00481  -0.0914   0.8756   0.0091
  -4.750  -0.1087   0.00928   0.00394  -0.0911   0.8703   0.0098
  -4.500  -0.0818   0.00886   0.00349  -0.0909   0.8644   0.0107
  -4.250  -0.0546   0.00851   0.00306  -0.0907   0.8588   0.0115
  -4.000  -0.0272   0.00821   0.00269  -0.0906   0.8530   0.0126
  -3.750   0.0003   0.00788   0.00229  -0.0905   0.8469   0.0157
  -3.500   0.0278   0.00762   0.00206  -0.0904   0.8409   0.0286
  -3.250   0.0555   0.00747   0.00193  -0.0903   0.8337   0.0384
  -3.000   0.0831   0.00732   0.00178  -0.0903   0.8263   0.0477
  -2.750   0.1107   0.00718   0.00163  -0.0902   0.8182   0.0577
  -2.500   0.1385   0.00702   0.00149  -0.0902   0.8109   0.0751
  -2.250   0.1658   0.00674   0.00136  -0.0902   0.8038   0.1264
  -2.000   0.1923   0.00613   0.00121  -0.0904   0.7968   0.2799
  -1.750   0.2183   0.00551   0.00110  -0.0904   0.7895   0.4622
  -1.500   0.2457   0.00533   0.00107  -0.0903   0.7810   0.5290
  -1.250   0.2731   0.00526   0.00104  -0.0902   0.7713   0.5671
  -1.000   0.3007   0.00524   0.00102  -0.0901   0.7612   0.5948
  -0.750   0.3286   0.00522   0.00101  -0.0900   0.7523   0.6176
  -0.500   0.3563   0.00522   0.00102  -0.0899   0.7444   0.6389
  -0.250   0.3840   0.00521   0.00104  -0.0898   0.7358   0.6634
   0.000   0.4116   0.00521   0.00107  -0.0897   0.7272   0.6892
   0.250   0.4390   0.00524   0.00109  -0.0895   0.7176   0.7049
   0.500   0.4666   0.00527   0.00110  -0.0894   0.7057   0.7176
   0.750   0.4941   0.00531   0.00112  -0.0893   0.6937   0.7283
   1.000   0.5217   0.00534   0.00115  -0.0892   0.6830   0.7370
   1.250   0.5493   0.00540   0.00118  -0.0891   0.6719   0.7457
   1.500   0.5766   0.00545   0.00122  -0.0890   0.6600   0.7549
   1.750   0.6038   0.00551   0.00126  -0.0888   0.6467   0.7643
   2.000   0.6310   0.00558   0.00131  -0.0886   0.6319   0.7743
   2.250   0.6579   0.00565   0.00137  -0.0885   0.6149   0.7850
   2.500   0.6845   0.00574   0.00144  -0.0882   0.5957   0.7964
   2.750   0.7105   0.00585   0.00152  -0.0878   0.5727   0.8090
   3.000   0.7360   0.00600   0.00162  -0.0874   0.5455   0.8236
   3.250   0.7610   0.00617   0.00173  -0.0868   0.5157   0.8413
   3.500   0.7845   0.00637   0.00187  -0.0860   0.4805   0.8660
   3.750   0.8087   0.00642   0.00201  -0.0852   0.4482   0.9519
   4.000   0.8380   0.00674   0.00219  -0.0858   0.4120   1.0000
   4.250   0.8629   0.00708   0.00238  -0.0854   0.3779   1.0000
   4.500   0.8875   0.00743   0.00258  -0.0849   0.3428   1.0000
   4.750   0.9118   0.00781   0.00280  -0.0845   0.3090   1.0000
   5.000   0.9360   0.00819   0.00305  -0.0840   0.2774   1.0000
   5.250   0.9595   0.00863   0.00331  -0.0834   0.2425   1.0000
   5.500   0.9828   0.00908   0.00359  -0.0828   0.2064   1.0000
   5.750   1.0067   0.00947   0.00385  -0.0822   0.1817   1.0000
   6.000   1.0305   0.00987   0.00414  -0.0817   0.1599   1.0000
   6.250   1.0544   0.01024   0.00443  -0.0812   0.1401   1.0000
   6.500   1.0775   0.01068   0.00475  -0.0805   0.1188   1.0000
   6.750   1.0996   0.01120   0.00513  -0.0797   0.0931   1.0000
   7.000   1.1209   0.01178   0.00556  -0.0788   0.0677   1.0000
   7.250   1.1423   0.01235   0.00600  -0.0779   0.0481   1.0000
   7.500   1.1631   0.01295   0.00651  -0.0769   0.0311   1.0000
   7.750   1.1837   0.01356   0.00703  -0.0759   0.0188   1.0000
   8.000   1.2026   0.01433   0.00770  -0.0746   0.0065   1.0000
   8.250   1.2237   0.01487   0.00825  -0.0735   0.0046   1.0000
   8.500   1.2451   0.01535   0.00880  -0.0726   0.0043   1.0000
   8.750   1.2654   0.01591   0.00943  -0.0714   0.0040   1.0000
   9.000   1.2853   0.01648   0.01007  -0.0702   0.0039   1.0000
   9.250   1.3039   0.01712   0.01080  -0.0689   0.0037   1.0000
   9.500   1.3217   0.01779   0.01155  -0.0674   0.0036   1.0000
   9.750   1.3379   0.01854   0.01238  -0.0657   0.0035   1.0000
  10.000   1.3508   0.01934   0.01327  -0.0634   0.0034   1.0000
  10.250   1.3619   0.02016   0.01417  -0.0608   0.0033   1.0000
  10.500   1.3705   0.02112   0.01523  -0.0580   0.0032   1.0000
  10.750   1.3776   0.02220   0.01640  -0.0551   0.0031   1.0000
  11.000   1.3833   0.02340   0.01771  -0.0523   0.0031   1.0000
  11.250   1.3878   0.02472   0.01914  -0.0495   0.0030   1.0000
  11.500   1.3901   0.02626   0.02080  -0.0466   0.0030   1.0000
  11.750   1.3905   0.02802   0.02270  -0.0439   0.0029   1.0000
  12.000   1.3912   0.02985   0.02466  -0.0414   0.0029   1.0000
  12.250   1.3927   0.03173   0.02666  -0.0393   0.0029   1.0000
  12.500   1.3896   0.03412   0.02918  -0.0372   0.0029   1.0000
  12.750   1.3875   0.03654   0.03174  -0.0354   0.0029   1.0000
  13.000   1.3844   0.03923   0.03456  -0.0339   0.0029   1.0000
  13.250   1.3751   0.04274   0.03824  -0.0326   0.0028   1.0000
  13.500   1.3733   0.04556   0.04119  -0.0319   0.0029   1.0000
  13.750   1.3638   0.04948   0.04528  -0.0313   0.0028   1.0000
  14.000   1.3642   0.05228   0.04818  -0.0313   0.0029   1.0000
  14.250   1.3549   0.05657   0.05264  -0.0317   0.0028   1.0000
  14.750   1.3515   0.06364   0.05995  -0.0335   0.0027   1.0000
  15.000   1.3432   0.06852   0.06498  -0.0351   0.0027   1.0000
  15.250   1.3225   0.07566   0.07231  -0.0377   0.0028   1.0000
  15.500   1.3145   0.08116   0.07794  -0.0402   0.0027   1.0000
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