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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.94 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1512-il-1000000-n5.txt
Download as CSV file: xf-hq1512-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.8630   0.11775   0.11553  -0.0166   1.0000   0.0044
 -17.000  -0.9320   0.10008   0.09769  -0.0261   1.0000   0.0042
 -16.750  -1.0182   0.07982   0.07718  -0.0375   1.0000   0.0038
 -16.500  -1.0653   0.06680   0.06394  -0.0455   1.0000   0.0039
 -16.250  -1.0965   0.05752   0.05447  -0.0516   1.0000   0.0039
 -16.000  -1.1195   0.05043   0.04720  -0.0561   1.0000   0.0039
 -15.750  -1.1253   0.04636   0.04303  -0.0583   1.0000   0.0039
 -15.500  -1.1391   0.04156   0.03806  -0.0608   1.0000   0.0039
 -15.250  -1.1421   0.03839   0.03479  -0.0620   1.0000   0.0039
 -15.000  -1.1401   0.03597   0.03228  -0.0626   1.0000   0.0042
 -14.750  -1.1408   0.03343   0.02961  -0.0631   1.0000   0.0042
 -14.500  -1.1423   0.03100   0.02706  -0.0631   1.0000   0.0043
 -14.250  -1.1377   0.02929   0.02527  -0.0627   1.0000   0.0043
 -14.000  -1.1358   0.02753   0.02340  -0.0619   1.0000   0.0043
 -13.750  -1.1324   0.02609   0.02185  -0.0607   1.0000   0.0044
 -13.500  -1.1298   0.02482   0.02049  -0.0588   1.0000   0.0044
 -13.250  -1.1237   0.02396   0.01955  -0.0565   1.0000   0.0045
 -13.000  -1.1173   0.02301   0.01851  -0.0540   1.0000   0.0046
 -12.750  -1.1075   0.02196   0.01737  -0.0522   1.0000   0.0048
 -12.500  -1.0936   0.02115   0.01648  -0.0507   1.0000   0.0050
 -12.250  -1.0782   0.02042   0.01570  -0.0493   1.0000   0.0052
 -12.000  -1.0609   0.01982   0.01506  -0.0481   1.0000   0.0054
 -11.750  -1.0436   0.01921   0.01440  -0.0468   1.0000   0.0056
 -11.500  -1.0258   0.01866   0.01380  -0.0455   1.0000   0.0058
 -11.250  -1.0081   0.01809   0.01318  -0.0442   1.0000   0.0061
 -11.000  -0.9812   0.01750   0.01253  -0.0447   0.9944   0.0064
 -10.750  -0.9514   0.01692   0.01186  -0.0458   0.9885   0.0066
 -10.500  -0.9196   0.01625   0.01113  -0.0473   0.9830   0.0068
 -10.250  -0.8890   0.01553   0.01035  -0.0486   0.9745   0.0073
 -10.000  -0.8568   0.01496   0.00974  -0.0501   0.9652   0.0077
  -9.750  -0.8255   0.01447   0.00919  -0.0513   0.9522   0.0080
  -9.500  -0.7977   0.01405   0.00870  -0.0517   0.9338   0.0084
  -9.250  -0.7730   0.01368   0.00822  -0.0513   0.9155   0.0088
  -9.000  -0.7491   0.01335   0.00780  -0.0507   0.9010   0.0091
  -8.750  -0.7248   0.01306   0.00742  -0.0502   0.8887   0.0094
  -8.500  -0.7014   0.01262   0.00690  -0.0496   0.8779   0.0101
  -8.250  -0.6772   0.01228   0.00651  -0.0491   0.8679   0.0108
  -8.000  -0.6523   0.01197   0.00614  -0.0487   0.8588   0.0114
  -7.750  -0.6270   0.01168   0.00577  -0.0483   0.8508   0.0119
  -7.500  -0.6015   0.01141   0.00545  -0.0479   0.8427   0.0125
  -7.250  -0.5757   0.01116   0.00514  -0.0477   0.8352   0.0130
  -7.000  -0.5503   0.01082   0.00476  -0.0473   0.8275   0.0143
  -6.750  -0.5243   0.01055   0.00446  -0.0470   0.8204   0.0153
  -6.500  -0.4981   0.01032   0.00417  -0.0468   0.8129   0.0164
  -6.250  -0.4716   0.01009   0.00390  -0.0466   0.8060   0.0179
  -6.000  -0.4453   0.00983   0.00364  -0.0464   0.7988   0.0210
  -5.750  -0.4187   0.00962   0.00340  -0.0462   0.7921   0.0246
  -5.500  -0.3920   0.00940   0.00317  -0.0460   0.7849   0.0295
  -5.250  -0.3653   0.00919   0.00296  -0.0458   0.7785   0.0354
  -5.000  -0.3382   0.00900   0.00277  -0.0457   0.7715   0.0414
  -4.750  -0.3114   0.00881   0.00258  -0.0456   0.7650   0.0499
  -4.500  -0.2843   0.00860   0.00240  -0.0455   0.7584   0.0610
  -4.250  -0.2573   0.00842   0.00223  -0.0454   0.7517   0.0736
  -4.000  -0.2300   0.00823   0.00208  -0.0453   0.7452   0.0890
  -3.750  -0.2031   0.00801   0.00193  -0.0452   0.7381   0.1104
  -3.500  -0.1760   0.00781   0.00178  -0.0451   0.7314   0.1339
  -3.250  -0.1493   0.00756   0.00164  -0.0450   0.7240   0.1699
  -3.000  -0.1220   0.00737   0.00153  -0.0450   0.7170   0.1981
  -2.750  -0.0947   0.00720   0.00142  -0.0449   0.7094   0.2262
  -2.500  -0.0676   0.00700   0.00131  -0.0449   0.7016   0.2627
  -2.000  -0.0148   0.00643   0.00108  -0.0446   0.6814   0.3846
  -1.750   0.0119   0.00619   0.00101  -0.0445   0.6729   0.4438
  -1.500   0.0393   0.00607   0.00096  -0.0444   0.6645   0.4810
  -1.250   0.0671   0.00599   0.00094  -0.0444   0.6556   0.5078
  -1.000   0.0948   0.00594   0.00091  -0.0443   0.6471   0.5315
  -0.750   0.1228   0.00589   0.00091  -0.0443   0.6382   0.5562
  -0.500   0.1506   0.00587   0.00091  -0.0443   0.6275   0.5761
  -0.250   0.1786   0.00588   0.00091  -0.0442   0.6171   0.5902
   0.000   0.2065   0.00589   0.00092  -0.0442   0.6052   0.6055
   0.250   0.2343   0.00593   0.00094  -0.0442   0.5908   0.6191
   0.500   0.2622   0.00597   0.00096  -0.0441   0.5776   0.6301
   0.750   0.2901   0.00600   0.00099  -0.0441   0.5651   0.6401
   1.000   0.3180   0.00606   0.00102  -0.0441   0.5511   0.6488
   1.250   0.3455   0.00614   0.00106  -0.0440   0.5333   0.6572
   1.500   0.3728   0.00625   0.00112  -0.0438   0.5127   0.6653
   1.750   0.4000   0.00636   0.00118  -0.0437   0.4913   0.6729
   2.000   0.4270   0.00652   0.00125  -0.0436   0.4665   0.6786
   2.250   0.4535   0.00670   0.00135  -0.0434   0.4380   0.6847
   2.500   0.4801   0.00690   0.00145  -0.0431   0.4090   0.6908
   2.750   0.5060   0.00714   0.00158  -0.0429   0.3749   0.6969
   3.000   0.5312   0.00745   0.00173  -0.0425   0.3310   0.7038
   3.250   0.5563   0.00778   0.00191  -0.0421   0.2917   0.7104
   3.500   0.5817   0.00806   0.00208  -0.0417   0.2624   0.7178
   3.750   0.6072   0.00833   0.00225  -0.0414   0.2377   0.7246
   4.000   0.6336   0.00851   0.00239  -0.0412   0.2213   0.7321
   4.250   0.6603   0.00866   0.00253  -0.0410   0.2109   0.7389
   4.500   0.6869   0.00880   0.00268  -0.0408   0.2014   0.7467
   4.750   0.7133   0.00896   0.00283  -0.0406   0.1906   0.7539
   5.000   0.7393   0.00915   0.00300  -0.0403   0.1782   0.7621
   5.250   0.7648   0.00937   0.00319  -0.0400   0.1621   0.7699
   5.500   0.7891   0.00970   0.00343  -0.0395   0.1382   0.7788
   5.750   0.8133   0.01001   0.00368  -0.0389   0.1170   0.7878
   6.000   0.8368   0.01039   0.00398  -0.0383   0.0959   0.7974
   6.250   0.8603   0.01074   0.00428  -0.0376   0.0779   0.8083
   6.500   0.8830   0.01113   0.00461  -0.0369   0.0613   0.8201
   6.750   0.9068   0.01140   0.00489  -0.0362   0.0528   0.8331
   7.000   0.9301   0.01168   0.00518  -0.0355   0.0456   0.8485
   7.250   0.9527   0.01193   0.00549  -0.0347   0.0403   0.8686
   7.500   0.9741   0.01208   0.00577  -0.0334   0.0370   0.9099
   7.750   1.0120   0.01235   0.00612  -0.0359   0.0338   1.0000
   8.000   1.0353   0.01270   0.00645  -0.0353   0.0307   1.0000
   8.250   1.0587   0.01302   0.00677  -0.0347   0.0281   1.0000
   8.500   1.0821   0.01333   0.00710  -0.0341   0.0260   1.0000
   8.750   1.1046   0.01370   0.00746  -0.0333   0.0232   1.0000
   9.000   1.1268   0.01408   0.00783  -0.0326   0.0208   1.0000
   9.250   1.1484   0.01449   0.00823  -0.0317   0.0179   1.0000
   9.500   1.1695   0.01491   0.00864  -0.0308   0.0158   1.0000
   9.750   1.1901   0.01535   0.00909  -0.0298   0.0134   1.0000
  10.000   1.2093   0.01586   0.00960  -0.0286   0.0102   1.0000
  10.250   1.2231   0.01672   0.01042  -0.0267   0.0042   1.0000
  10.500   1.2403   0.01729   0.01102  -0.0252   0.0038   1.0000
  10.750   1.2550   0.01784   0.01162  -0.0232   0.0035   1.0000
  11.000   1.2687   0.01840   0.01223  -0.0211   0.0032   1.0000
  11.250   1.2814   0.01902   0.01290  -0.0190   0.0030   1.0000
  11.500   1.2947   0.01963   0.01356  -0.0170   0.0028   1.0000
  11.750   1.3073   0.02030   0.01431  -0.0151   0.0028   1.0000
  12.000   1.3197   0.02100   0.01507  -0.0133   0.0026   1.0000
  12.250   1.3312   0.02180   0.01592  -0.0115   0.0026   1.0000
  12.500   1.3424   0.02263   0.01682  -0.0098   0.0025   1.0000
  12.750   1.3525   0.02358   0.01784  -0.0081   0.0024   1.0000
  13.000   1.3620   0.02460   0.01894  -0.0065   0.0024   1.0000
  13.250   1.3706   0.02574   0.02015  -0.0049   0.0023   1.0000
  13.500   1.3792   0.02691   0.02140  -0.0035   0.0023   1.0000
  13.750   1.3858   0.02828   0.02285  -0.0021   0.0022   1.0000
  14.000   1.3916   0.02979   0.02446  -0.0008   0.0021   1.0000
  14.250   1.3971   0.03137   0.02612   0.0003   0.0021   1.0000
  14.500   1.4015   0.03312   0.02795   0.0013   0.0021   1.0000
  14.750   1.4044   0.03507   0.03000   0.0021   0.0020   1.0000
  15.000   1.4066   0.03718   0.03221   0.0028   0.0020   1.0000
  15.250   1.4071   0.03953   0.03465   0.0033   0.0020   1.0000
  15.500   1.4060   0.04216   0.03739   0.0036   0.0019   1.0000
  15.750   1.4010   0.04533   0.04068   0.0036   0.0019   1.0000
  16.000   1.3946   0.04884   0.04432   0.0033   0.0018   1.0000
  16.250   1.3923   0.05205   0.04763   0.0027   0.0019   1.0000
  16.500   1.3814   0.05655   0.05226   0.0015   0.0018   1.0000
  16.750   1.3687   0.06163   0.05748  -0.0002   0.0018   1.0000
  17.000   1.3614   0.06616   0.06213  -0.0020   0.0018   1.0000
  17.250   1.3477   0.07196   0.06806  -0.0045   0.0018   1.0000
  17.500   1.3235   0.07991   0.07619  -0.0084   0.0017   1.0000
  17.750   1.3108   0.08614   0.08255  -0.0116   0.0018   1.0000
  18.000   1.2945   0.09329   0.08983  -0.0153   0.0018   1.0000
  18.250   1.2726   0.10179   0.09848  -0.0200   0.0018   1.0000
  18.500   1.2470   0.11123   0.10807  -0.0252   0.0018   1.0000
  18.750   1.2207   0.12105   0.11804  -0.0307   0.0018   1.0000
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