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HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 50,000
Max Cl/Cd: 31.96 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1012-il-50000-n5.txt
Download as CSV file: xf-hq1012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5962   0.09804   0.09087  -0.0280   1.0000   0.0537
 -11.250  -0.6121   0.08973   0.08264  -0.0332   1.0000   0.0534
 -11.000  -0.6328   0.08176   0.07466  -0.0386   1.0000   0.0530
 -10.750  -0.6558   0.07482   0.06769  -0.0431   1.0000   0.0525
 -10.500  -0.6789   0.06914   0.06191  -0.0462   1.0000   0.0521
 -10.250  -0.7013   0.06447   0.05712  -0.0474   1.0000   0.0519
 -10.000  -0.7216   0.06063   0.05311  -0.0466   1.0000   0.0520
  -9.750  -0.7362   0.05672   0.04893  -0.0455   1.0000   0.0524
  -9.500  -0.7459   0.05287   0.04469  -0.0441   1.0000   0.0533
  -9.250  -0.7516   0.04927   0.04055  -0.0423   1.0000   0.0549
  -9.000  -0.7413   0.04708   0.03843  -0.0413   1.0000   0.0580
  -8.750  -0.7327   0.04479   0.03594  -0.0399   1.0000   0.0613
  -8.500  -0.7240   0.04194   0.03263  -0.0383   1.0000   0.0647
  -8.250  -0.7128   0.03943   0.02974  -0.0367   1.0000   0.0689
  -8.000  -0.6981   0.03778   0.02807  -0.0354   1.0000   0.0742
  -7.750  -0.6825   0.03572   0.02558  -0.0338   1.0000   0.0799
  -7.500  -0.6665   0.03419   0.02410  -0.0325   1.0000   0.0863
  -7.250  -0.6488   0.03261   0.02220  -0.0309   1.0000   0.0935
  -7.000  -0.6322   0.03129   0.02097  -0.0294   1.0000   0.1012
  -6.750  -0.6145   0.03002   0.01951  -0.0277   1.0000   0.1098
  -6.500  -0.5977   0.02886   0.01834  -0.0259   1.0000   0.1177
  -6.250  -0.5831   0.02784   0.01733  -0.0240   1.0000   0.1284
  -6.000  -0.5696   0.02691   0.01639  -0.0219   1.0000   0.1410
  -5.750  -0.5568   0.02598   0.01549  -0.0197   1.0000   0.1546
  -5.500  -0.5451   0.02511   0.01469  -0.0175   1.0000   0.1739
  -5.250  -0.5337   0.02421   0.01391  -0.0154   1.0000   0.1991
  -5.000  -0.5220   0.02329   0.01311  -0.0133   1.0000   0.2330
  -4.750  -0.5102   0.02232   0.01241  -0.0114   1.0000   0.2816
  -4.500  -0.4985   0.02141   0.01195  -0.0094   1.0000   0.3481
  -4.250  -0.4872   0.02086   0.01185  -0.0068   1.0000   0.4322
  -4.000  -0.4667   0.02076   0.01206  -0.0052   0.9958   0.5194
  -3.750  -0.4372   0.02099   0.01231  -0.0052   0.9871   0.5902
  -3.500  -0.4079   0.02134   0.01260  -0.0048   0.9787   0.6411
  -3.250  -0.3775   0.02172   0.01289  -0.0046   0.9709   0.6820
  -3.000  -0.3501   0.02199   0.01305  -0.0039   0.9622   0.7129
  -2.750  -0.3185   0.02221   0.01309  -0.0042   0.9550   0.7390
  -2.500  -0.2898   0.02233   0.01308  -0.0040   0.9466   0.7595
  -2.250  -0.2584   0.02243   0.01303  -0.0045   0.9392   0.7798
  -2.000  -0.2285   0.02253   0.01301  -0.0045   0.9314   0.7995
  -1.750  -0.1969   0.02267   0.01305  -0.0047   0.9243   0.8212
  -1.500  -0.1650   0.02276   0.01305  -0.0051   0.9169   0.8419
  -1.250  -0.1276   0.02281   0.01299  -0.0068   0.9104   0.8575
  -1.000  -0.0922   0.02281   0.01290  -0.0085   0.9028   0.8704
  -0.750  -0.0498   0.02284   0.01282  -0.0115   0.8968   0.8819
  -0.500  -0.0118   0.02287   0.01279  -0.0137   0.8889   0.8932
  -0.250   0.0332   0.02289   0.01274  -0.0172   0.8829   0.9036
   0.000   0.0711   0.02292   0.01274  -0.0195   0.8742   0.9149
   0.250   0.1178   0.02293   0.01272  -0.0234   0.8677   0.9244
   0.500   0.1604   0.02296   0.01275  -0.0266   0.8591   0.9343
   0.750   0.2042   0.02297   0.01275  -0.0300   0.8513   0.9443
   1.000   0.2498   0.02296   0.01276  -0.0338   0.8429   0.9535
   1.250   0.2933   0.02297   0.01282  -0.0373   0.8333   0.9630
   1.500   0.3387   0.02285   0.01275  -0.0408   0.8241   0.9724
   1.750   0.3823   0.02261   0.01258  -0.0436   0.8108   0.9820
   2.000   0.4218   0.02235   0.01237  -0.0457   0.7933   0.9930
   2.250   0.4505   0.02215   0.01222  -0.0458   0.7758   1.0000
   2.500   0.4648   0.02211   0.01223  -0.0435   0.7602   1.0000
   2.750   0.4788   0.02212   0.01228  -0.0411   0.7456   1.0000
   3.000   0.4934   0.02215   0.01234  -0.0388   0.7308   1.0000
   3.250   0.5092   0.02218   0.01241  -0.0365   0.7156   1.0000
   3.500   0.5265   0.02221   0.01248  -0.0345   0.6998   1.0000
   3.750   0.5458   0.02221   0.01255  -0.0326   0.6832   1.0000
   4.000   0.5671   0.02217   0.01256  -0.0310   0.6658   1.0000
   4.250   0.5880   0.02217   0.01261  -0.0293   0.6464   1.0000
   4.500   0.6083   0.02220   0.01274  -0.0275   0.6240   1.0000
   4.750   0.6296   0.02220   0.01280  -0.0258   0.5997   1.0000
   5.000   0.6513   0.02218   0.01282  -0.0241   0.5721   1.0000
   5.250   0.6725   0.02223   0.01288  -0.0223   0.5402   1.0000
   5.500   0.6941   0.02230   0.01293  -0.0206   0.5048   1.0000
   5.750   0.7143   0.02256   0.01308  -0.0188   0.4663   1.0000
   6.000   0.7339   0.02296   0.01332  -0.0170   0.4282   1.0000
   6.250   0.7521   0.02356   0.01378  -0.0153   0.3912   1.0000
   6.500   0.7695   0.02429   0.01434  -0.0137   0.3575   1.0000
   6.750   0.7863   0.02511   0.01506  -0.0121   0.3262   1.0000
   7.000   0.8026   0.02601   0.01584  -0.0105   0.2981   1.0000
   7.250   0.8188   0.02699   0.01675  -0.0091   0.2716   1.0000
   7.500   0.8351   0.02803   0.01777  -0.0077   0.2470   1.0000
   7.750   0.8513   0.02913   0.01879  -0.0064   0.2251   1.0000
   8.000   0.8673   0.03024   0.01998  -0.0050   0.2029   1.0000
   8.250   0.8821   0.03138   0.02114  -0.0036   0.1838   1.0000
   8.500   0.8979   0.03259   0.02236  -0.0023   0.1669   1.0000
   8.750   0.9130   0.03385   0.02367  -0.0010   0.1513   1.0000
   9.000   0.9287   0.03520   0.02503   0.0002   0.1385   1.0000
   9.250   0.9444   0.03661   0.02647   0.0013   0.1274   1.0000
   9.500   0.9591   0.03814   0.02815   0.0025   0.1163   1.0000
   9.750   0.9755   0.03989   0.03009   0.0036   0.1074   1.0000
  10.000   0.9898   0.04153   0.03165   0.0047   0.0996   1.0000
  10.250   0.9986   0.04346   0.03393   0.0063   0.0917   1.0000
  10.500   1.0105   0.04534   0.03579   0.0075   0.0857   1.0000
  10.750   1.0147   0.04764   0.03847   0.0093   0.0797   1.0000
  11.000   1.0227   0.04954   0.04034   0.0105   0.0748   1.0000
  11.250   1.0242   0.05251   0.04365   0.0119   0.0711   1.0000
  11.500   1.0201   0.05552   0.04699   0.0133   0.0675   1.0000
  11.750   1.0183   0.05810   0.04968   0.0141   0.0641   1.0000
  12.000   1.0212   0.06078   0.05234   0.0147   0.0611   1.0000
  12.250   1.0066   0.06515   0.05709   0.0148   0.0601   1.0000
  12.500   0.9881   0.07015   0.06241   0.0141   0.0593   1.0000
  12.750   0.9670   0.07583   0.06837   0.0123   0.0589   1.0000
  13.000   0.9428   0.08250   0.07526   0.0093   0.0589   1.0000
  13.250   0.9160   0.09037   0.08330   0.0049   0.0593   1.0000
  13.500   0.8862   0.09985   0.09292  -0.0009   0.0599   1.0000
  13.750   0.8565   0.11070   0.10383  -0.0076   0.0606   1.0000
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