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HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/8 AIRFOIL (hq108-il)
Reynolds number: 500,000
Max Cl/Cd: 63.85 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq108-il-500000-n5.txt
Download as CSV file: xf-hq108-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5746   0.08135   0.07915  -0.0134   1.0000   0.0030
  -8.750  -0.5841   0.07481   0.07266  -0.0177   1.0000   0.0028
  -8.500  -0.6014   0.06668   0.06458  -0.0256   1.0000   0.0028
  -8.250  -0.6173   0.05891   0.05671  -0.0310   1.0000   0.0027
  -8.000  -0.6290   0.05029   0.04787  -0.0339   1.0000   0.0025
  -7.750  -0.6346   0.04203   0.03930  -0.0347   1.0000   0.0025
  -7.500  -0.6359   0.03376   0.03057  -0.0341   1.0000   0.0025
  -7.250  -0.6256   0.02934   0.02576  -0.0333   1.0000   0.0027
  -7.000  -0.6105   0.02633   0.02241  -0.0323   1.0000   0.0029
  -6.750  -0.5935   0.02378   0.01952  -0.0312   1.0000   0.0031
  -6.500  -0.5750   0.02167   0.01711  -0.0301   1.0000   0.0033
  -6.250  -0.5556   0.01989   0.01506  -0.0289   1.0000   0.0036
  -6.000  -0.5337   0.01816   0.01306  -0.0280   0.9991   0.0038
  -5.750  -0.5023   0.01676   0.01143  -0.0291   0.9937   0.0042
  -5.500  -0.4703   0.01608   0.01062  -0.0303   0.9885   0.0048
  -5.250  -0.4370   0.01555   0.00996  -0.0316   0.9836   0.0051
  -5.000  -0.4070   0.01386   0.00801  -0.0322   0.9764   0.0052
  -4.750  -0.3760   0.01256   0.00654  -0.0330   0.9693   0.0052
  -4.500  -0.3455   0.01146   0.00529  -0.0337   0.9604   0.0053
  -4.250  -0.3157   0.01059   0.00427  -0.0342   0.9500   0.0055
  -4.000  -0.2861   0.00999   0.00353  -0.0346   0.9388   0.0060
  -3.750  -0.2573   0.00956   0.00297  -0.0346   0.9267   0.0075
  -3.500  -0.2299   0.00912   0.00256  -0.0345   0.9146   0.0227
  -3.250  -0.2032   0.00882   0.00227  -0.0343   0.9029   0.0474
  -3.000  -0.1776   0.00835   0.00204  -0.0341   0.8914   0.1059
  -2.750  -0.1520   0.00790   0.00182  -0.0338   0.8798   0.1789
  -2.500  -0.1260   0.00757   0.00163  -0.0336   0.8689   0.2419
  -2.250  -0.1002   0.00719   0.00146  -0.0333   0.8582   0.3176
  -2.000  -0.0747   0.00679   0.00131  -0.0331   0.8472   0.4130
  -1.750  -0.0492   0.00646   0.00120  -0.0327   0.8355   0.5018
  -1.500  -0.0236   0.00622   0.00116  -0.0322   0.8240   0.5772
  -1.250   0.0027   0.00608   0.00115  -0.0318   0.8133   0.6289
  -1.000   0.0291   0.00599   0.00114  -0.0314   0.8018   0.6699
  -0.750   0.0558   0.00597   0.00111  -0.0310   0.7877   0.6917
  -0.500   0.0826   0.00597   0.00106  -0.0307   0.7723   0.7092
  -0.250   0.1094   0.00597   0.00105  -0.0303   0.7578   0.7288
   0.000   0.1361   0.00596   0.00105  -0.0300   0.7435   0.7483
   0.250   0.1629   0.00596   0.00105  -0.0296   0.7275   0.7651
   0.500   0.1898   0.00598   0.00105  -0.0294   0.7103   0.7774
   0.750   0.2169   0.00601   0.00107  -0.0291   0.6950   0.7885
   1.000   0.2439   0.00604   0.00108  -0.0289   0.6797   0.8002
   1.250   0.2707   0.00608   0.00111  -0.0286   0.6637   0.8126
   1.500   0.2974   0.00612   0.00115  -0.0283   0.6448   0.8260
   1.750   0.3236   0.00618   0.00119  -0.0278   0.6225   0.8405
   2.000   0.3493   0.00626   0.00126  -0.0273   0.5900   0.8567
   2.250   0.3742   0.00640   0.00133  -0.0266   0.5482   0.8763
   2.500   0.3983   0.00663   0.00142  -0.0258   0.4898   0.9016
   2.750   0.4255   0.00703   0.00157  -0.0258   0.4104   0.9360
   3.000   0.4612   0.00743   0.00175  -0.0278   0.3431   0.9746
   3.250   0.4920   0.00787   0.00198  -0.0288   0.2817   1.0000
   3.750   0.5429   0.00855   0.00240  -0.0283   0.2124   1.0000
   4.000   0.5683   0.00890   0.00263  -0.0280   0.1772   1.0000
   4.250   0.5931   0.00937   0.00289  -0.0277   0.1293   1.0000
   4.500   0.6180   0.00983   0.00323  -0.0274   0.0939   1.0000
   4.750   0.6428   0.01030   0.00357  -0.0270   0.0643   1.0000
   5.000   0.6681   0.01070   0.00391  -0.0267   0.0478   1.0000
   5.250   0.6935   0.01109   0.00428  -0.0264   0.0352   1.0000
   5.500   0.7186   0.01153   0.00470  -0.0260   0.0246   1.0000
   5.750   0.7439   0.01193   0.00511  -0.0257   0.0190   1.0000
   6.000   0.7684   0.01251   0.00573  -0.0252   0.0142   1.0000
   6.250   0.7939   0.01284   0.00611  -0.0249   0.0116   1.0000
   6.500   0.8183   0.01338   0.00673  -0.0244   0.0089   1.0000
   6.750   0.8415   0.01419   0.00765  -0.0237   0.0066   1.0000
   7.000   0.8653   0.01483   0.00839  -0.0231   0.0054   1.0000
   7.250   0.8895   0.01535   0.00895  -0.0227   0.0044   1.0000
   7.500   0.9112   0.01632   0.01000  -0.0220   0.0033   1.0000
   7.750   0.9342   0.01704   0.01084  -0.0213   0.0030   1.0000
   8.000   0.9560   0.01798   0.01192  -0.0205   0.0027   1.0000
   8.250   0.9770   0.01906   0.01317  -0.0196   0.0025   1.0000
   8.500   0.9979   0.02011   0.01436  -0.0188   0.0022   1.0000
   8.750   1.0186   0.02114   0.01553  -0.0180   0.0020   1.0000
   9.000   1.0381   0.02235   0.01691  -0.0171   0.0018   1.0000
   9.250   1.0568   0.02359   0.01837  -0.0161   0.0016   1.0000
   9.500   1.0705   0.02564   0.02069  -0.0146   0.0014   1.0000
   9.750   1.0756   0.02906   0.02457  -0.0123   0.0013   1.0000
  10.250   1.0742   0.03618   0.03252  -0.0073   0.0013   1.0000
  10.500   1.0671   0.03934   0.03600  -0.0044   0.0013   1.0000
  10.750   1.0509   0.04263   0.03956  -0.0012   0.0012   1.0000
  11.000   1.0301   0.04672   0.04388   0.0002   0.0013   1.0000
  11.250   1.0114   0.05131   0.04867  -0.0004   0.0013   1.0000
  11.500   0.9921   0.05713   0.05468  -0.0033   0.0013   1.0000
  11.750   0.9703   0.06509   0.06281  -0.0091   0.0013   1.0000
  12.250   0.9501   0.08245   0.08040  -0.0218   0.0013   1.0000
  12.500   0.9378   0.09161   0.08960  -0.0268   0.0014   1.0000
  12.750   0.9243   0.10034   0.09836  -0.0310   0.0015   1.0000
  13.000   0.8217   0.13471   0.13261  -0.0463   0.0017   1.0000
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