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HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/7 AIRFOIL (hq07-il)
Reynolds number: 100,000
Max Cl/Cd: 31.36 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq07-il-100000-n5.txt
Download as CSV file: xf-hq07-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/7 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6682   0.08759   0.08286   0.0050   1.0000   0.0125
  -8.750  -0.6738   0.08131   0.07664   0.0004   1.0000   0.0122
  -8.500  -0.6837   0.07408   0.06944  -0.0060   1.0000   0.0119
  -8.250  -0.6959   0.06802   0.06330  -0.0093   1.0000   0.0115
  -8.000  -0.7029   0.06213   0.05726  -0.0114   1.0000   0.0112
  -7.750  -0.7056   0.05664   0.05152  -0.0125   1.0000   0.0109
  -7.500  -0.7040   0.05145   0.04603  -0.0128   1.0000   0.0107
  -7.250  -0.6982   0.04662   0.04081  -0.0127   1.0000   0.0106
  -7.000  -0.6889   0.04215   0.03590  -0.0122   1.0000   0.0105
  -6.750  -0.6761   0.03805   0.03131  -0.0114   1.0000   0.0105
  -6.500  -0.6605   0.03426   0.02701  -0.0106   1.0000   0.0107
  -6.250  -0.6424   0.03090   0.02316  -0.0097   1.0000   0.0111
  -6.000  -0.6217   0.02803   0.01986  -0.0088   1.0000   0.0117
  -5.750  -0.5993   0.02554   0.01699  -0.0079   1.0000   0.0127
  -5.500  -0.5755   0.02390   0.01505  -0.0071   1.0000   0.0165
  -5.250  -0.5521   0.02221   0.01312  -0.0064   1.0000   0.0227
  -5.000  -0.5282   0.02092   0.01163  -0.0057   1.0000   0.0333
  -4.750  -0.5058   0.01917   0.00982  -0.0046   1.0000   0.0392
  -4.500  -0.4829   0.01790   0.00835  -0.0035   1.0000   0.0448
  -4.250  -0.4598   0.01695   0.00731  -0.0028   1.0000   0.0563
  -4.000  -0.4371   0.01592   0.00633  -0.0020   1.0000   0.0739
  -3.750  -0.4147   0.01481   0.00528  -0.0012   1.0000   0.1159
  -3.500  -0.3948   0.01346   0.00465  -0.0004   1.0000   0.2605
  -3.250  -0.3783   0.01205   0.00433   0.0013   1.0000   0.4791
  -3.000  -0.3602   0.01148   0.00433   0.0038   1.0000   0.6284
  -2.750  -0.3401   0.01127   0.00428   0.0061   1.0000   0.7075
  -2.500  -0.3203   0.01114   0.00425   0.0086   1.0000   0.7659
  -2.250  -0.2995   0.01104   0.00415   0.0106   1.0000   0.8046
  -2.000  -0.2765   0.01094   0.00398   0.0119   1.0000   0.8282
  -1.750  -0.2530   0.01084   0.00381   0.0130   1.0000   0.8500
  -1.500  -0.2283   0.01077   0.00360   0.0139   1.0000   0.8747
  -1.250  -0.1984   0.01075   0.00356   0.0139   1.0000   0.9035
  -1.000  -0.1614   0.01076   0.00353   0.0122   1.0000   0.9309
  -0.750  -0.1216   0.01075   0.00347   0.0095   1.0000   0.9512
  -0.500  -0.0814   0.01074   0.00340   0.0066   1.0000   0.9680
  -0.250  -0.0401   0.01071   0.00335   0.0033   1.0000   0.9827
   0.000   0.0000   0.01069   0.00332   0.0000   1.0000   1.0000
   0.250   0.0401   0.01070   0.00334  -0.0033   0.9827   1.0000
   0.500   0.0814   0.01073   0.00340  -0.0066   0.9680   1.0000
   0.750   0.1215   0.01075   0.00347  -0.0095   0.9511   1.0000
   1.000   0.1614   0.01075   0.00352  -0.0122   0.9308   1.0000
   1.250   0.1982   0.01075   0.00356  -0.0138   0.9035   1.0000
   1.500   0.2279   0.01077   0.00360  -0.0139   0.8747   1.0000
   1.750   0.2526   0.01084   0.00380  -0.0129   0.8499   1.0000
   2.000   0.2761   0.01094   0.00397  -0.0119   0.8282   1.0000
   2.250   0.2990   0.01104   0.00415  -0.0106   0.8047   1.0000
   2.500   0.3199   0.01114   0.00424  -0.0085   0.7663   1.0000
   2.750   0.3396   0.01127   0.00428  -0.0060   0.7078   1.0000
   3.000   0.3598   0.01148   0.00433  -0.0037   0.6298   1.0000
   3.250   0.3779   0.01205   0.00433  -0.0012   0.4796   1.0000
   3.500   0.3943   0.01348   0.00466   0.0005   0.2580   1.0000
   3.750   0.4145   0.01480   0.00527   0.0012   0.1165   1.0000
   4.000   0.4369   0.01592   0.00633   0.0020   0.0740   1.0000
   4.250   0.4598   0.01695   0.00731   0.0028   0.0564   1.0000
   4.500   0.4829   0.01791   0.00835   0.0035   0.0447   1.0000
   4.750   0.5058   0.01919   0.00984   0.0046   0.0391   1.0000
   5.000   0.5285   0.02090   0.01162   0.0057   0.0336   1.0000
   5.250   0.5523   0.02222   0.01313   0.0063   0.0227   1.0000
   5.500   0.5757   0.02391   0.01505   0.0071   0.0165   1.0000
   5.750   0.5996   0.02557   0.01701   0.0078   0.0127   1.0000
   6.000   0.6220   0.02805   0.01987   0.0087   0.0116   1.0000
   6.250   0.6427   0.03092   0.02318   0.0096   0.0110   1.0000
   6.500   0.6611   0.03429   0.02705   0.0105   0.0107   1.0000
   6.750   0.6766   0.03809   0.03136   0.0113   0.0105   1.0000
   7.000   0.6892   0.04225   0.03600   0.0120   0.0105   1.0000
   7.250   0.6989   0.04669   0.04089   0.0125   0.0106   1.0000
   7.500   0.7045   0.05152   0.04610   0.0126   0.0107   1.0000
   7.750   0.7064   0.05678   0.05168   0.0122   0.0110   1.0000
   8.000   0.7039   0.06223   0.05736   0.0112   0.0112   1.0000
   8.250   0.6967   0.06818   0.06347   0.0090   0.0115   1.0000
   8.500   0.6844   0.07427   0.06963   0.0056   0.0119   1.0000
   8.750   0.6750   0.08136   0.07668  -0.0007   0.0121   1.0000
   9.000   0.6695   0.08765   0.08292  -0.0053   0.0124   1.0000
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