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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 200,000
Max Cl/Cd: 60.33 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1512-il-200000-n5.txt
Download as CSV file: xf-hq1512-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7468   0.05858   0.05432  -0.0547   1.0000   0.0134
 -12.000  -0.7643   0.05323   0.04879  -0.0579   1.0000   0.0134
 -11.750  -0.7872   0.04783   0.04312  -0.0601   1.0000   0.0133
 -11.500  -0.7930   0.04513   0.04031  -0.0606   1.0000   0.0135
 -11.250  -0.8011   0.04244   0.03748  -0.0602   1.0000   0.0137
 -11.000  -0.8084   0.04021   0.03510  -0.0588   1.0000   0.0139
 -10.750  -0.8144   0.03828   0.03301  -0.0564   1.0000   0.0141
 -10.500  -0.8152   0.03611   0.03061  -0.0544   1.0000   0.0143
 -10.250  -0.8112   0.03427   0.02857  -0.0525   1.0000   0.0148
 -10.000  -0.8053   0.03234   0.02641  -0.0505   1.0000   0.0152
  -9.750  -0.7973   0.03055   0.02438  -0.0486   1.0000   0.0156
  -9.500  -0.7874   0.02897   0.02256  -0.0465   1.0000   0.0162
  -9.250  -0.7758   0.02768   0.02104  -0.0445   1.0000   0.0170
  -9.000  -0.7654   0.02628   0.01951  -0.0424   1.0000   0.0178
  -8.750  -0.7544   0.02536   0.01856  -0.0403   1.0000   0.0185
  -8.500  -0.7307   0.02426   0.01737  -0.0405   0.9960   0.0194
  -8.250  -0.7006   0.02298   0.01594  -0.0419   0.9891   0.0205
  -8.000  -0.6689   0.02175   0.01454  -0.0435   0.9834   0.0218
  -7.750  -0.6389   0.02071   0.01333  -0.0446   0.9763   0.0233
  -7.500  -0.6073   0.01967   0.01226  -0.0462   0.9706   0.0254
  -7.250  -0.5783   0.01883   0.01135  -0.0470   0.9620   0.0273
  -7.000  -0.5460   0.01798   0.01037  -0.0484   0.9560   0.0296
  -6.750  -0.5185   0.01713   0.00948  -0.0489   0.9465   0.0327
  -6.500  -0.4878   0.01651   0.00878  -0.0499   0.9391   0.0372
  -6.250  -0.4593   0.01582   0.00805  -0.0504   0.9304   0.0427
  -6.000  -0.4304   0.01529   0.00744  -0.0509   0.9223   0.0500
  -5.750  -0.4019   0.01474   0.00690  -0.0513   0.9145   0.0612
  -5.500  -0.3750   0.01426   0.00642  -0.0514   0.9059   0.0750
  -5.250  -0.3475   0.01378   0.00598  -0.0515   0.8986   0.0942
  -5.000  -0.3225   0.01333   0.00562  -0.0512   0.8895   0.1200
  -4.750  -0.2967   0.01287   0.00526  -0.0511   0.8820   0.1527
  -4.250  -0.2466   0.01206   0.00465  -0.0504   0.8661   0.2312
  -4.000  -0.2221   0.01163   0.00436  -0.0500   0.8582   0.2787
  -3.750  -0.1986   0.01110   0.00411  -0.0494   0.8510   0.3514
  -3.500  -0.1752   0.01066   0.00397  -0.0487   0.8432   0.4361
  -3.250  -0.1504   0.01042   0.00391  -0.0480   0.8364   0.5005
  -3.000  -0.1249   0.01031   0.00388  -0.0474   0.8289   0.5451
  -2.750  -0.0983   0.01026   0.00383  -0.0469   0.8225   0.5753
  -2.500  -0.0717   0.01023   0.00379  -0.0465   0.8149   0.5986
  -2.250  -0.0446   0.01022   0.00374  -0.0461   0.8087   0.6187
  -2.000  -0.0180   0.01021   0.00373  -0.0457   0.8010   0.6371
  -1.750   0.0092   0.01021   0.00367  -0.0453   0.7949   0.6528
  -1.500   0.0361   0.01021   0.00366  -0.0450   0.7870   0.6661
  -1.250   0.0634   0.01021   0.00362  -0.0446   0.7807   0.6794
  -1.000   0.0901   0.01022   0.00363  -0.0442   0.7728   0.6933
  -0.750   0.1173   0.01023   0.00360  -0.0439   0.7663   0.7064
  -0.500   0.1439   0.01023   0.00362  -0.0434   0.7577   0.7173
  -0.250   0.1708   0.01023   0.00358  -0.0430   0.7490   0.7273
   0.000   0.1978   0.01022   0.00354  -0.0427   0.7385   0.7366
   0.250   0.2246   0.01021   0.00353  -0.0423   0.7283   0.7435
   0.500   0.2520   0.01022   0.00348  -0.0420   0.7189   0.7515
   0.750   0.2787   0.01021   0.00348  -0.0416   0.7085   0.7584
   1.000   0.3057   0.01022   0.00347  -0.0413   0.6974   0.7666
   1.250   0.3323   0.01022   0.00348  -0.0409   0.6861   0.7740
   1.500   0.3592   0.01024   0.00348  -0.0406   0.6755   0.7823
   1.750   0.3858   0.01025   0.00351  -0.0402   0.6649   0.7902
   2.000   0.4125   0.01027   0.00357  -0.0398   0.6541   0.7986
   2.250   0.4390   0.01030   0.00361  -0.0394   0.6425   0.8075
   2.500   0.4652   0.01033   0.00366  -0.0390   0.6299   0.8163
   2.750   0.4915   0.01037   0.00372  -0.0385   0.6165   0.8260
   3.000   0.5173   0.01040   0.00379  -0.0380   0.6011   0.8361
   3.250   0.5430   0.01045   0.00386  -0.0374   0.5836   0.8467
   3.500   0.5686   0.01051   0.00394  -0.0368   0.5636   0.8586
   3.750   0.5938   0.01060   0.00403  -0.0361   0.5404   0.8720
   4.000   0.6189   0.01073   0.00412  -0.0355   0.5121   0.8878
   4.250   0.6449   0.01093   0.00425  -0.0350   0.4769   0.9070
   4.500   0.6744   0.01125   0.00445  -0.0355   0.4328   0.9314
   4.750   0.7071   0.01172   0.00472  -0.0369   0.3823   0.9681
   5.000   0.7337   0.01228   0.00503  -0.0373   0.3330   1.0000
   5.250   0.7538   0.01283   0.00538  -0.0362   0.2972   1.0000
   5.500   0.7752   0.01332   0.00573  -0.0354   0.2717   1.0000
   5.750   0.7970   0.01378   0.00610  -0.0346   0.2523   1.0000
   6.000   0.8198   0.01418   0.00646  -0.0339   0.2349   1.0000
   6.250   0.8426   0.01458   0.00685  -0.0333   0.2185   1.0000
   6.500   0.8654   0.01498   0.00723  -0.0326   0.2022   1.0000
   6.750   0.8875   0.01541   0.00763  -0.0318   0.1833   1.0000
   7.000   0.9088   0.01591   0.00806  -0.0310   0.1600   1.0000
   7.250   0.9286   0.01653   0.00855  -0.0300   0.1328   1.0000
   7.500   0.9473   0.01725   0.00915  -0.0288   0.1093   1.0000
   7.750   0.9662   0.01794   0.00978  -0.0277   0.0925   1.0000
   8.000   0.9846   0.01865   0.01045  -0.0265   0.0801   1.0000
   8.250   1.0022   0.01940   0.01116  -0.0252   0.0712   1.0000
   8.500   1.0207   0.02005   0.01186  -0.0240   0.0648   1.0000
   8.750   1.0363   0.02087   0.01269  -0.0224   0.0600   1.0000
   9.000   1.0534   0.02155   0.01346  -0.0210   0.0566   1.0000
   9.250   1.0689   0.02225   0.01424  -0.0194   0.0532   1.0000
   9.500   1.0814   0.02306   0.01508  -0.0174   0.0504   1.0000
   9.750   1.0912   0.02404   0.01608  -0.0152   0.0476   1.0000
  10.000   1.1063   0.02473   0.01688  -0.0136   0.0451   1.0000
  10.250   1.1200   0.02551   0.01774  -0.0121   0.0423   1.0000
  10.500   1.1317   0.02642   0.01870  -0.0105   0.0395   1.0000
  10.750   1.1395   0.02765   0.01996  -0.0086   0.0375   1.0000
  11.000   1.1524   0.02856   0.02101  -0.0073   0.0361   1.0000
  11.250   1.1635   0.02964   0.02222  -0.0059   0.0348   1.0000
  11.500   1.1738   0.03081   0.02350  -0.0046   0.0335   1.0000
  11.750   1.1845   0.03193   0.02472  -0.0035   0.0316   1.0000
  12.000   1.1926   0.03330   0.02615  -0.0023   0.0300   1.0000
  12.250   1.1992   0.03485   0.02777  -0.0012   0.0283   1.0000
  12.500   1.2090   0.03619   0.02928  -0.0004   0.0268   1.0000
  12.750   1.2183   0.03761   0.03086   0.0004   0.0249   1.0000
  13.000   1.2267   0.03912   0.03246   0.0009   0.0229   1.0000
  13.250   1.2314   0.04103   0.03444   0.0015   0.0212   1.0000
  13.500   1.2373   0.04292   0.03651   0.0020   0.0196   1.0000
  13.750   1.2434   0.04485   0.03853   0.0022   0.0173   1.0000
  14.000   1.2449   0.04731   0.04107   0.0023   0.0155   1.0000
  14.250   1.2453   0.05001   0.04393   0.0023   0.0141   1.0000
  14.500   1.2437   0.05305   0.04710   0.0020   0.0130   1.0000
  14.750   1.2394   0.05654   0.05070   0.0013   0.0122   1.0000
  15.000   1.2330   0.06049   0.05478   0.0003   0.0115   1.0000
  15.250   1.2254   0.06483   0.05930  -0.0011   0.0109   1.0000
  15.500   1.2165   0.06960   0.06424  -0.0029   0.0104   1.0000
  15.750   1.2055   0.07501   0.06982  -0.0053   0.0099   1.0000
  16.000   1.1932   0.08091   0.07589  -0.0082   0.0096   1.0000
  16.250   1.1792   0.08739   0.08255  -0.0115   0.0096   1.0000
  16.500   1.1634   0.09457   0.08990  -0.0154   0.0094   1.0000
  16.750   1.1452   0.10248   0.09798  -0.0198   0.0093   1.0000
  17.000   1.1265   0.11078   0.10645  -0.0244   0.0094   1.0000
  17.250   1.1069   0.11947   0.11531  -0.0293   0.0095   1.0000
  17.500   1.0841   0.12918   0.12517  -0.0349   0.0095   1.0000
  17.750   1.0631   0.13871   0.13486  -0.0404   0.0097   1.0000
  18.000   1.0403   0.14905   0.14535  -0.0464   0.0099   1.0000
  18.250   1.0159   0.16033   0.15676  -0.0529   0.0102   1.0000
  18.500   0.9865   0.17373   0.17030  -0.0604   0.0104   1.0000
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