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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 500,000
Max Cl/Cd: 84.76 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159b-il-500000.txt
Download as CSV file: xf-hq159b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 B AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.6011   0.03980   0.03681  -0.0445   1.0000   0.0135
  -7.500  -0.6044   0.03387   0.03049  -0.0428   1.0000   0.0128
  -7.250  -0.6089   0.02665   0.02259  -0.0397   1.0000   0.0119
  -7.000  -0.6001   0.02358   0.01912  -0.0372   1.0000   0.0120
  -6.750  -0.5879   0.02199   0.01731  -0.0349   1.0000   0.0126
  -6.500  -0.5554   0.01923   0.01413  -0.0365   0.9971   0.0130
  -6.250  -0.5221   0.01681   0.01136  -0.0381   0.9943   0.0133
  -6.000  -0.4890   0.01542   0.00974  -0.0393   0.9906   0.0141
  -5.750  -0.4568   0.01345   0.00756  -0.0406   0.9869   0.0154
  -5.500  -0.4210   0.01271   0.00677  -0.0426   0.9840   0.0176
  -5.250  -0.3853   0.01225   0.00624  -0.0443   0.9808   0.0205
  -5.000  -0.3519   0.01146   0.00545  -0.0458   0.9762   0.0268
  -4.750  -0.3168   0.01077   0.00470  -0.0475   0.9724   0.0330
  -4.500  -0.2803   0.01051   0.00441  -0.0494   0.9692   0.0390
  -4.250  -0.2504   0.01002   0.00390  -0.0500   0.9614   0.0457
  -4.000  -0.2171   0.00976   0.00361  -0.0511   0.9559   0.0521
  -3.750  -0.1897   0.00931   0.00315  -0.0511   0.9459   0.0629
  -3.500  -0.1622   0.00896   0.00279  -0.0509   0.9363   0.0789
  -3.250  -0.1362   0.00843   0.00245  -0.0506   0.9269   0.1269
  -3.000  -0.1129   0.00764   0.00218  -0.0501   0.9157   0.2664
  -2.750  -0.0898   0.00686   0.00197  -0.0496   0.9052   0.4358
  -2.500  -0.0652   0.00646   0.00186  -0.0489   0.8958   0.5356
  -2.250  -0.0397   0.00628   0.00184  -0.0483   0.8864   0.6035
  -2.000  -0.0136   0.00621   0.00182  -0.0477   0.8764   0.6453
  -1.750   0.0128   0.00619   0.00179  -0.0472   0.8665   0.6736
  -1.250   0.0660   0.00617   0.00174  -0.0462   0.8462   0.7148
  -1.000   0.0926   0.00615   0.00173  -0.0457   0.8364   0.7328
  -0.750   0.1191   0.00615   0.00172  -0.0452   0.8267   0.7507
  -0.500   0.1458   0.00613   0.00170  -0.0448   0.8165   0.7657
  -0.250   0.1727   0.00612   0.00170  -0.0444   0.8065   0.7797
   0.000   0.1995   0.00611   0.00168  -0.0440   0.7965   0.7919
   0.250   0.2264   0.00611   0.00165  -0.0436   0.7855   0.8034
   0.500   0.2533   0.00609   0.00164  -0.0432   0.7739   0.8152
   1.000   0.3069   0.00607   0.00165  -0.0425   0.7536   0.8414
   1.250   0.3334   0.00606   0.00167  -0.0420   0.7437   0.8551
   1.500   0.3598   0.00603   0.00169  -0.0416   0.7327   0.8697
   1.750   0.3857   0.00601   0.00172  -0.0410   0.7215   0.8870
   2.000   0.4112   0.00598   0.00175  -0.0403   0.7090   0.9093
   2.250   0.4390   0.00597   0.00178  -0.0400   0.6928   0.9391
   2.500   0.4763   0.00601   0.00179  -0.0419   0.6682   0.9704
   2.750   0.5125   0.00613   0.00179  -0.0438   0.6287   1.0000
   3.000   0.5374   0.00634   0.00185  -0.0433   0.5837   1.0000
   3.250   0.5619   0.00663   0.00194  -0.0427   0.5302   1.0000
   3.500   0.5856   0.00706   0.00210  -0.0420   0.4681   1.0000
   3.750   0.6090   0.00757   0.00232  -0.0414   0.4025   1.0000
   4.000   0.6318   0.00820   0.00258  -0.0408   0.3198   1.0000
   4.250   0.6560   0.00868   0.00287  -0.0403   0.2735   1.0000
   4.500   0.6811   0.00907   0.00313  -0.0400   0.2421   1.0000
   4.750   0.7062   0.00945   0.00340  -0.0397   0.2116   1.0000
   5.000   0.7309   0.00989   0.00368  -0.0393   0.1689   1.0000
   5.250   0.7513   0.01093   0.00424  -0.0384   0.0792   1.0000
   5.500   0.7738   0.01171   0.00481  -0.0377   0.0438   1.0000
   5.750   0.7981   0.01227   0.00537  -0.0371   0.0371   1.0000
   6.000   0.8227   0.01273   0.00589  -0.0366   0.0337   1.0000
   6.250   0.8461   0.01337   0.00656  -0.0359   0.0301   1.0000
   6.500   0.8681   0.01419   0.00749  -0.0350   0.0272   1.0000
   6.750   0.8918   0.01475   0.00812  -0.0344   0.0252   1.0000
   7.000   0.9147   0.01540   0.00881  -0.0337   0.0225   1.0000
   7.250   0.9303   0.01718   0.01069  -0.0320   0.0191   1.0000
   7.500   0.9547   0.01761   0.01119  -0.0314   0.0179   1.0000
   7.750   0.9768   0.01839   0.01206  -0.0306   0.0162   1.0000
   8.000   0.9986   0.01918   0.01292  -0.0298   0.0148   1.0000
   8.250   1.0177   0.02045   0.01424  -0.0287   0.0138   1.0000
   8.500   1.0337   0.02282   0.01680  -0.0272   0.0126   1.0000
   8.750   1.0560   0.02329   0.01739  -0.0264   0.0117   1.0000
   9.000   1.0755   0.02456   0.01881  -0.0254   0.0110   1.0000
   9.250   1.0942   0.02577   0.02015  -0.0243   0.0104   1.0000
   9.500   1.1115   0.02716   0.02168  -0.0231   0.0099   1.0000
   9.750   1.1275   0.02848   0.02315  -0.0219   0.0095   1.0000
  10.000   1.1401   0.03041   0.02523  -0.0203   0.0092   1.0000
  10.250   1.1439   0.03396   0.02911  -0.0180   0.0089   1.0000
  10.500   1.1372   0.03853   0.03410  -0.0149   0.0087   1.0000
  10.750   1.1267   0.04215   0.03803  -0.0113   0.0087   1.0000
  11.000   1.1141   0.04506   0.04117  -0.0078   0.0087   1.0000
  11.250   1.0983   0.04835   0.04470  -0.0051   0.0087   1.0000
  11.500   1.0763   0.05265   0.04924  -0.0036   0.0087   1.0000
  11.750   1.0701   0.05538   0.05211  -0.0033   0.0087   1.0000
  12.000   1.0588   0.05912   0.05601  -0.0039   0.0088   1.0000
  12.250   1.0360   0.06503   0.06212  -0.0061   0.0088   1.0000
  12.500   1.0242   0.06999   0.06721  -0.0087   0.0088   1.0000
  12.750   1.0039   0.07723   0.07462  -0.0134   0.0088   1.0000
  13.000   0.9946   0.08339   0.08091  -0.0179   0.0089   1.0000
  13.250   0.9681   0.09515   0.09290  -0.0265   0.0092   1.0000
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