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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 200,000
Max Cl/Cd: 67.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1512-il-200000.txt
Download as CSV file: xf-hq1512-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4659   0.07445   0.07117  -0.0424   1.0000   0.0486
 -10.250  -0.4530   0.07419   0.07092  -0.0411   1.0000   0.0514
 -10.000  -0.6646   0.05631   0.05229  -0.0577   1.0000   0.0354
  -9.750  -0.6816   0.05257   0.04846  -0.0559   1.0000   0.0347
  -9.500  -0.6955   0.04865   0.04435  -0.0541   1.0000   0.0339
  -9.250  -0.7080   0.04456   0.03999  -0.0517   1.0000   0.0332
  -9.000  -0.7176   0.04049   0.03557  -0.0487   1.0000   0.0323
  -8.750  -0.7230   0.03686   0.03156  -0.0454   1.0000   0.0319
  -8.500  -0.7242   0.03407   0.02844  -0.0419   1.0000   0.0319
  -8.250  -0.7234   0.03190   0.02598  -0.0383   1.0000   0.0322
  -8.000  -0.7194   0.03051   0.02438  -0.0351   1.0000   0.0335
  -7.750  -0.7134   0.02916   0.02276  -0.0320   1.0000   0.0347
  -7.500  -0.7048   0.02782   0.02111  -0.0293   1.0000   0.0356
  -7.250  -0.6755   0.02547   0.01837  -0.0303   0.9967   0.0366
  -7.000  -0.6423   0.02289   0.01569  -0.0322   0.9931   0.0389
  -6.750  -0.6071   0.02186   0.01458  -0.0342   0.9880   0.0425
  -6.500  -0.5692   0.02082   0.01334  -0.0364   0.9839   0.0459
  -6.250  -0.5371   0.01902   0.01155  -0.0378   0.9791   0.0502
  -6.000  -0.5012   0.01832   0.01076  -0.0397   0.9736   0.0573
  -5.750  -0.4647   0.01707   0.00958  -0.0420   0.9698   0.0679
  -5.500  -0.4336   0.01623   0.00874  -0.0431   0.9629   0.0830
  -5.250  -0.3982   0.01526   0.00789  -0.0452   0.9581   0.1087
  -5.000  -0.3594   0.01433   0.00720  -0.0481   0.9550   0.1537
  -4.750  -0.3319   0.01354   0.00674  -0.0487   0.9470   0.2149
  -4.500  -0.2980   0.01263   0.00624  -0.0506   0.9424   0.3036
  -4.250  -0.2717   0.01183   0.00599  -0.0509   0.9354   0.4278
  -4.000  -0.2417   0.01148   0.00595  -0.0512   0.9291   0.5236
  -3.750  -0.2084   0.01139   0.00595  -0.0520   0.9245   0.5786
  -3.500  -0.1817   0.01143   0.00597  -0.0514   0.9163   0.6133
  -3.250  -0.1492   0.01145   0.00596  -0.0518   0.9114   0.6420
  -3.000  -0.1238   0.01154   0.00605  -0.0509   0.9031   0.6626
  -2.750  -0.0939   0.01157   0.00604  -0.0508   0.8974   0.6813
  -2.500  -0.0682   0.01165   0.00608  -0.0500   0.8894   0.6968
  -2.250  -0.0401   0.01168   0.00608  -0.0496   0.8830   0.7117
  -2.000  -0.0148   0.01175   0.00613  -0.0487   0.8752   0.7259
  -1.750   0.0122   0.01177   0.00612  -0.0480   0.8685   0.7390
  -1.500   0.0377   0.01182   0.00614  -0.0472   0.8609   0.7510
  -1.250   0.0643   0.01182   0.00609  -0.0466   0.8539   0.7631
  -1.000   0.0895   0.01186   0.00613  -0.0457   0.8465   0.7746
  -0.750   0.1150   0.01187   0.00614  -0.0447   0.8394   0.7865
  -0.500   0.1398   0.01188   0.00615  -0.0437   0.8315   0.7981
  -0.250   0.1656   0.01181   0.00605  -0.0428   0.8233   0.8095
   0.000   0.1902   0.01176   0.00599  -0.0418   0.8134   0.8197
   0.250   0.2167   0.01164   0.00584  -0.0411   0.8054   0.8278
   0.500   0.2420   0.01157   0.00575  -0.0404   0.7955   0.8374
   0.750   0.2674   0.01147   0.00567  -0.0395   0.7863   0.8460
   1.000   0.2938   0.01134   0.00551  -0.0388   0.7776   0.8552
   1.250   0.3185   0.01127   0.00545  -0.0379   0.7669   0.8658
   1.500   0.3442   0.01118   0.00538  -0.0371   0.7584   0.8753
   1.750   0.3699   0.01109   0.00531  -0.0364   0.7494   0.8861
   2.000   0.3951   0.01102   0.00528  -0.0356   0.7394   0.8978
   2.250   0.4218   0.01095   0.00521  -0.0350   0.7306   0.9103
   2.500   0.4501   0.01088   0.00518  -0.0347   0.7198   0.9223
   2.750   0.4812   0.01083   0.00518  -0.0351   0.7081   0.9351
   3.000   0.5162   0.01078   0.00516  -0.0364   0.6960   0.9476
   3.250   0.5543   0.01074   0.00513  -0.0384   0.6825   0.9598
   3.500   0.5942   0.01070   0.00512  -0.0408   0.6668   0.9717
   3.750   0.6355   0.01067   0.00510  -0.0435   0.6487   0.9833
   4.000   0.6781   0.01064   0.00505  -0.0466   0.6272   0.9949
   4.250   0.7002   0.01063   0.00504  -0.0460   0.6031   1.0000
   4.500   0.7161   0.01071   0.00503  -0.0439   0.5765   1.0000
   4.750   0.7359   0.01087   0.00505  -0.0424   0.5414   1.0000
   5.000   0.7557   0.01116   0.00514  -0.0409   0.4948   1.0000
   5.250   0.7746   0.01161   0.00534  -0.0393   0.4418   1.0000
   5.500   0.7934   0.01217   0.00563  -0.0378   0.3945   1.0000
   5.750   0.8132   0.01273   0.00600  -0.0366   0.3556   1.0000
   6.000   0.8336   0.01328   0.00639  -0.0355   0.3252   1.0000
   6.250   0.8542   0.01383   0.00683  -0.0345   0.3000   1.0000
   6.500   0.8750   0.01438   0.00728  -0.0335   0.2786   1.0000
   6.750   0.8960   0.01492   0.00776  -0.0325   0.2589   1.0000
   7.000   0.9171   0.01541   0.00824  -0.0316   0.2372   1.0000
   7.250   0.9374   0.01593   0.00872  -0.0306   0.2118   1.0000
   7.500   0.9562   0.01654   0.00922  -0.0293   0.1775   1.0000
   7.750   0.9716   0.01745   0.00990  -0.0277   0.1380   1.0000
   8.000   0.9852   0.01854   0.01079  -0.0258   0.1129   1.0000
   8.250   0.9997   0.01955   0.01172  -0.0239   0.0989   1.0000
   8.500   1.0133   0.02062   0.01273  -0.0220   0.0901   1.0000
   8.750   1.0291   0.02151   0.01367  -0.0204   0.0835   1.0000
   9.000   1.0422   0.02277   0.01487  -0.0185   0.0784   1.0000
   9.250   1.0587   0.02359   0.01580  -0.0169   0.0741   1.0000
   9.500   1.0734   0.02454   0.01676  -0.0153   0.0703   1.0000
   9.750   1.0912   0.02622   0.01838  -0.0143   0.0666   1.0000
  10.000   1.1091   0.02719   0.01950  -0.0130   0.0645   1.0000
  10.250   1.1273   0.02835   0.02080  -0.0118   0.0620   1.0000
  10.500   1.1440   0.02947   0.02199  -0.0106   0.0594   1.0000
  10.750   1.1635   0.03115   0.02363  -0.0102   0.0560   1.0000
  11.000   1.1752   0.03240   0.02507  -0.0084   0.0535   1.0000
  11.250   1.1836   0.03327   0.02611  -0.0062   0.0510   1.0000
  11.500   1.1909   0.03415   0.02707  -0.0043   0.0483   1.0000
  11.750   1.2010   0.03543   0.02833  -0.0030   0.0456   1.0000
  12.000   1.2100   0.03747   0.03057  -0.0016   0.0434   1.0000
  12.250   1.2140   0.03874   0.03205   0.0003   0.0416   1.0000
  12.500   1.2182   0.04028   0.03376   0.0019   0.0397   1.0000
  12.750   1.2216   0.04171   0.03528   0.0032   0.0376   1.0000
  13.000   1.2272   0.04374   0.03730   0.0041   0.0355   1.0000
  13.250   1.2220   0.04643   0.04026   0.0054   0.0336   1.0000
  13.500   1.2175   0.04868   0.04274   0.0063   0.0314   1.0000
  13.750   1.2152   0.05081   0.04494   0.0066   0.0292   1.0000
  14.000   1.2154   0.05323   0.04736   0.0068   0.0277   1.0000
  14.250   1.2035   0.05720   0.05155   0.0066   0.0259   1.0000
  14.500   1.1944   0.06111   0.05571   0.0061   0.0249   1.0000
  14.750   1.1848   0.06513   0.05994   0.0051   0.0236   1.0000
  15.000   1.1760   0.06935   0.06431   0.0037   0.0227   1.0000
  15.250   1.1668   0.07392   0.06903   0.0020   0.0222   1.0000
  15.500   1.1625   0.07778   0.07292   0.0003   0.0213   1.0000
  15.750   1.1513   0.08317   0.07844  -0.0021   0.0210   1.0000
  16.000   1.1341   0.08986   0.08530  -0.0053   0.0206   1.0000
  16.250   1.1147   0.09738   0.09303  -0.0094   0.0205   1.0000
  16.500   1.0953   0.10542   0.10127  -0.0142   0.0205   1.0000
  16.750   1.0739   0.11448   0.11057  -0.0201   0.0208   1.0000
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