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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 100,000
Max Cl/Cd: 49.15 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1510-il-100000-n5.txt
Download as CSV file: xf-hq1510-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5222   0.09158   0.08661  -0.0256   1.0000   0.0211
  -9.750  -0.5272   0.08598   0.08107  -0.0287   1.0000   0.0208
  -9.500  -0.5347   0.07961   0.07476  -0.0326   1.0000   0.0207
  -9.250  -0.5461   0.07162   0.06683  -0.0387   1.0000   0.0202
  -9.000  -0.5641   0.06461   0.05980  -0.0442   1.0000   0.0197
  -8.750  -0.5848   0.05949   0.05461  -0.0462   1.0000   0.0195
  -8.500  -0.5993   0.05448   0.04941  -0.0470   1.0000   0.0194
  -8.250  -0.6076   0.04986   0.04454  -0.0469   1.0000   0.0193
  -8.000  -0.6111   0.04557   0.03991  -0.0461   1.0000   0.0196
  -7.750  -0.6095   0.04179   0.03576  -0.0448   1.0000   0.0201
  -7.500  -0.6042   0.03842   0.03195  -0.0432   1.0000   0.0215
  -7.250  -0.5958   0.03528   0.02828  -0.0413   1.0000   0.0227
  -7.000  -0.5843   0.03260   0.02511  -0.0394   1.0000   0.0234
  -6.750  -0.5724   0.02968   0.02187  -0.0376   1.0000   0.0241
  -6.500  -0.5582   0.02770   0.01970  -0.0359   1.0000   0.0252
  -6.250  -0.5425   0.02616   0.01798  -0.0342   1.0000   0.0267
  -6.000  -0.5260   0.02475   0.01637  -0.0325   1.0000   0.0288
  -5.750  -0.5087   0.02365   0.01501  -0.0308   1.0000   0.0324
  -5.500  -0.4914   0.02232   0.01355  -0.0294   0.9998   0.0359
  -5.250  -0.4582   0.02100   0.01213  -0.0309   0.9943   0.0420
  -5.000  -0.4257   0.01998   0.01105  -0.0323   0.9881   0.0520
  -4.750  -0.3925   0.01907   0.01007  -0.0339   0.9825   0.0644
  -4.500  -0.3604   0.01829   0.00924  -0.0353   0.9759   0.0788
  -4.250  -0.3264   0.01751   0.00842  -0.0369   0.9705   0.0943
  -4.000  -0.2956   0.01679   0.00771  -0.0379   0.9633   0.1165
  -3.750  -0.2613   0.01596   0.00711  -0.0398   0.9582   0.1675
  -3.500  -0.2328   0.01503   0.00663  -0.0407   0.9508   0.2698
  -3.250  -0.2035   0.01401   0.00645  -0.0417   0.9451   0.4581
  -3.000  -0.1761   0.01374   0.00648  -0.0413   0.9376   0.5658
  -2.750  -0.1446   0.01368   0.00647  -0.0416   0.9314   0.6287
  -2.500  -0.1165   0.01368   0.00648  -0.0413   0.9238   0.6740
  -2.250  -0.0863   0.01370   0.00652  -0.0411   0.9175   0.7148
  -2.000  -0.0589   0.01373   0.00649  -0.0405   0.9098   0.7437
  -1.750  -0.0277   0.01370   0.00639  -0.0407   0.9035   0.7641
  -1.500  -0.0008   0.01369   0.00635  -0.0401   0.8954   0.7857
  -1.250   0.0289   0.01364   0.00627  -0.0399   0.8890   0.8063
  -1.000   0.0555   0.01361   0.00618  -0.0394   0.8802   0.8218
  -0.750   0.0872   0.01353   0.00603  -0.0399   0.8739   0.8344
  -0.500   0.1138   0.01349   0.00596  -0.0394   0.8645   0.8473
  -0.250   0.1432   0.01342   0.00585  -0.0395   0.8568   0.8602
   0.000   0.1723   0.01337   0.00578  -0.0395   0.8484   0.8736
   0.250   0.2014   0.01333   0.00574  -0.0395   0.8396   0.8878
   0.500   0.2342   0.01325   0.00566  -0.0401   0.8322   0.9018
   0.750   0.2668   0.01321   0.00564  -0.0409   0.8214   0.9166
   1.000   0.3023   0.01313   0.00555  -0.0421   0.8091   0.9318
   1.250   0.3391   0.01302   0.00544  -0.0436   0.7948   0.9484
   1.500   0.3766   0.01291   0.00531  -0.0453   0.7794   0.9661
   1.750   0.4145   0.01283   0.00523  -0.0473   0.7646   0.9863
   2.000   0.4449   0.01283   0.00524  -0.0480   0.7509   1.0000
   2.250   0.4670   0.01289   0.00528  -0.0470   0.7374   1.0000
   2.500   0.4906   0.01295   0.00534  -0.0461   0.7230   1.0000
   2.750   0.5149   0.01302   0.00541  -0.0454   0.7079   1.0000
   3.000   0.5398   0.01309   0.00547  -0.0447   0.6916   1.0000
   3.250   0.5644   0.01320   0.00562  -0.0439   0.6730   1.0000
   3.500   0.5892   0.01329   0.00573  -0.0432   0.6525   1.0000
   3.750   0.6138   0.01341   0.00585  -0.0423   0.6291   1.0000
   4.000   0.6381   0.01355   0.00599  -0.0414   0.6013   1.0000
   4.250   0.6621   0.01373   0.00615  -0.0404   0.5672   1.0000
   4.500   0.6851   0.01399   0.00628  -0.0393   0.5237   1.0000
   4.750   0.7068   0.01438   0.00647  -0.0380   0.4699   1.0000
   5.000   0.7272   0.01494   0.00676  -0.0366   0.4122   1.0000
   5.250   0.7473   0.01560   0.00719  -0.0354   0.3573   1.0000
   5.500   0.7676   0.01629   0.00767  -0.0343   0.3112   1.0000
   5.750   0.7881   0.01700   0.00821  -0.0333   0.2732   1.0000
   6.000   0.8090   0.01770   0.00880  -0.0324   0.2402   1.0000
   6.250   0.8306   0.01835   0.00942  -0.0316   0.2086   1.0000
   6.500   0.8513   0.01908   0.01006  -0.0307   0.1732   1.0000
   6.750   0.8708   0.01998   0.01083  -0.0297   0.1341   1.0000
   7.000   0.8892   0.02102   0.01171  -0.0286   0.1069   1.0000
   7.250   0.9076   0.02209   0.01272  -0.0274   0.0919   1.0000
   7.500   0.9261   0.02313   0.01380  -0.0262   0.0811   1.0000
   7.750   0.9448   0.02415   0.01490  -0.0250   0.0723   1.0000
   8.000   0.9614   0.02536   0.01611  -0.0237   0.0660   1.0000
   8.250   0.9798   0.02648   0.01742  -0.0225   0.0613   1.0000
   8.500   0.9971   0.02773   0.01877  -0.0212   0.0572   1.0000
   8.750   1.0134   0.02915   0.02032  -0.0199   0.0524   1.0000
   9.000   1.0304   0.03006   0.02141  -0.0189   0.0453   1.0000
   9.250   1.0452   0.03122   0.02271  -0.0176   0.0390   1.0000
   9.500   1.0592   0.03218   0.02378  -0.0164   0.0328   1.0000
   9.750   1.0710   0.03382   0.02563  -0.0148   0.0281   1.0000
  10.000   1.0801   0.03547   0.02745  -0.0128   0.0243   1.0000
  10.250   1.0835   0.03742   0.02948  -0.0105   0.0221   1.0000
  10.500   1.0898   0.03987   0.03222  -0.0085   0.0201   1.0000
  10.750   1.0942   0.04230   0.03493  -0.0065   0.0185   1.0000
  11.000   1.0958   0.04449   0.03733  -0.0048   0.0171   1.0000
  11.250   1.0957   0.04676   0.03976  -0.0034   0.0162   1.0000
  11.500   1.0935   0.04904   0.04221  -0.0025   0.0153   1.0000
  11.750   1.0866   0.05230   0.04561  -0.0018   0.0146   1.0000
  12.000   1.0797   0.05598   0.04961  -0.0015   0.0142   1.0000
  12.250   1.0696   0.06017   0.05409  -0.0018   0.0139   1.0000
  12.500   1.0575   0.06486   0.05904  -0.0029   0.0138   1.0000
  12.750   1.0416   0.07044   0.06487  -0.0050   0.0136   1.0000
  13.000   1.0250   0.07659   0.07124  -0.0081   0.0136   1.0000
  13.250   1.0044   0.08414   0.07902  -0.0126   0.0136   1.0000
  13.500   0.9861   0.09191   0.08693  -0.0174   0.0140   1.0000
  13.750   0.9646   0.10123   0.09640  -0.0235   0.0142   1.0000
  14.000   0.9451   0.11066   0.10586  -0.0293   0.0146   1.0000
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