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HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il)
Reynolds number: 50,000
Max Cl/Cd: 33.63 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1512-il-50000-n5.txt
Download as CSV file: xf-hq1512-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5312   0.10621   0.09890  -0.0317   1.0000   0.0504
 -11.250  -0.5354   0.10029   0.09303  -0.0345   1.0000   0.0502
 -11.000  -0.5419   0.09393   0.08671  -0.0378   1.0000   0.0500
 -10.750  -0.5533   0.08695   0.07977  -0.0420   1.0000   0.0497
 -10.500  -0.5681   0.08030   0.07313  -0.0463   1.0000   0.0494
 -10.250  -0.5868   0.07416   0.06697  -0.0502   1.0000   0.0490
 -10.000  -0.6078   0.06892   0.06172  -0.0529   1.0000   0.0487
  -9.750  -0.6290   0.06474   0.05746  -0.0536   1.0000   0.0485
  -9.500  -0.6471   0.06097   0.05356  -0.0529   1.0000   0.0484
  -9.250  -0.6604   0.05716   0.04951  -0.0519   1.0000   0.0486
  -9.000  -0.6697   0.05348   0.04551  -0.0505   1.0000   0.0491
  -8.750  -0.6748   0.05005   0.04166  -0.0487   1.0000   0.0500
  -8.500  -0.6724   0.04716   0.03854  -0.0470   1.0000   0.0515
  -8.250  -0.6644   0.04515   0.03646  -0.0454   1.0000   0.0538
  -8.000  -0.6568   0.04288   0.03397  -0.0435   1.0000   0.0559
  -7.750  -0.6479   0.04039   0.03117  -0.0415   1.0000   0.0577
  -7.500  -0.6368   0.03799   0.02840  -0.0395   1.0000   0.0599
  -7.250  -0.6243   0.03593   0.02594  -0.0374   1.0000   0.0632
  -7.000  -0.6116   0.03452   0.02459  -0.0357   1.0000   0.0674
  -6.750  -0.5972   0.03300   0.02286  -0.0337   1.0000   0.0722
  -6.500  -0.5813   0.03147   0.02109  -0.0317   1.0000   0.0770
  -6.250  -0.5678   0.03037   0.02001  -0.0298   1.0000   0.0840
  -6.000  -0.5532   0.02922   0.01878  -0.0277   1.0000   0.0923
  -5.750  -0.5387   0.02824   0.01768  -0.0257   1.0000   0.1034
  -5.500  -0.5249   0.02726   0.01669  -0.0238   1.0000   0.1166
  -5.250  -0.5114   0.02629   0.01580  -0.0220   1.0000   0.1329
  -5.000  -0.4976   0.02535   0.01495  -0.0202   1.0000   0.1538
  -4.750  -0.4833   0.02442   0.01413  -0.0187   1.0000   0.1835
  -4.500  -0.4591   0.02335   0.01329  -0.0193   0.9960   0.2344
  -4.250  -0.4302   0.02212   0.01256  -0.0208   0.9888   0.3176
  -4.000  -0.4035   0.02139   0.01256  -0.0211   0.9816   0.4442
  -3.750  -0.3770   0.02142   0.01286  -0.0203   0.9736   0.5467
  -3.500  -0.3491   0.02169   0.01310  -0.0197   0.9658   0.6106
  -3.250  -0.3202   0.02200   0.01329  -0.0193   0.9582   0.6574
  -3.000  -0.2940   0.02226   0.01343  -0.0184   0.9502   0.6935
  -2.750  -0.2646   0.02253   0.01355  -0.0179   0.9432   0.7248
  -2.500  -0.2396   0.02267   0.01356  -0.0170   0.9350   0.7513
  -2.250  -0.2086   0.02283   0.01359  -0.0169   0.9285   0.7745
  -2.000  -0.1835   0.02289   0.01353  -0.0162   0.9203   0.7965
  -1.750  -0.1514   0.02300   0.01353  -0.0163   0.9142   0.8198
  -1.500  -0.1251   0.02306   0.01351  -0.0156   0.9063   0.8426
  -1.250  -0.0881   0.02312   0.01345  -0.0170   0.9004   0.8618
  -1.000  -0.0544   0.02313   0.01335  -0.0183   0.8930   0.8760
  -0.750  -0.0145   0.02314   0.01327  -0.0208   0.8867   0.8889
  -0.500   0.0249   0.02318   0.01320  -0.0234   0.8800   0.9015
  -0.250   0.0657   0.02321   0.01317  -0.0262   0.8728   0.9139
   0.000   0.1122   0.02325   0.01313  -0.0300   0.8669   0.9249
   0.250   0.1550   0.02331   0.01316  -0.0334   0.8589   0.9365
   0.500   0.2045   0.02330   0.01311  -0.0378   0.8530   0.9468
   0.750   0.2468   0.02336   0.01317  -0.0412   0.8440   0.9589
   1.000   0.2938   0.02335   0.01316  -0.0453   0.8367   0.9700
   1.250   0.3387   0.02335   0.01319  -0.0491   0.8278   0.9820
   1.500   0.3814   0.02332   0.01320  -0.0525   0.8174   0.9959
   1.750   0.4063   0.02324   0.01313  -0.0523   0.8045   1.0000
   2.000   0.4232   0.02312   0.01303  -0.0503   0.7892   1.0000
   2.250   0.4408   0.02299   0.01289  -0.0484   0.7735   1.0000
   2.500   0.4595   0.02289   0.01277  -0.0465   0.7583   1.0000
   2.750   0.4797   0.02287   0.01278  -0.0450   0.7443   1.0000
   3.000   0.5018   0.02289   0.01281  -0.0438   0.7308   1.0000
   3.250   0.5251   0.02290   0.01285  -0.0427   0.7170   1.0000
   3.500   0.5487   0.02291   0.01290  -0.0416   0.7023   1.0000
   3.750   0.5722   0.02294   0.01300  -0.0405   0.6868   1.0000
   4.000   0.5960   0.02295   0.01307  -0.0394   0.6702   1.0000
   4.250   0.6204   0.02293   0.01312  -0.0383   0.6526   1.0000
   4.500   0.6460   0.02286   0.01311  -0.0372   0.6342   1.0000
   4.750   0.6679   0.02294   0.01330  -0.0358   0.6123   1.0000
   5.000   0.6929   0.02288   0.01329  -0.0346   0.5897   1.0000
   5.250   0.7150   0.02297   0.01345  -0.0331   0.5631   1.0000
   5.750   0.7610   0.02318   0.01367  -0.0303   0.5030   1.0000
   6.000   0.7828   0.02345   0.01386  -0.0288   0.4697   1.0000
   6.250   0.8030   0.02388   0.01420  -0.0272   0.4356   1.0000
   6.500   0.8220   0.02445   0.01462  -0.0256   0.4025   1.0000
   6.750   0.8395   0.02514   0.01520  -0.0239   0.3707   1.0000
   7.000   0.8557   0.02592   0.01587  -0.0223   0.3404   1.0000
   7.250   0.8708   0.02680   0.01663  -0.0206   0.3115   1.0000
   7.500   0.8852   0.02775   0.01750  -0.0189   0.2842   1.0000
   7.750   0.8988   0.02878   0.01849  -0.0172   0.2579   1.0000
   8.000   0.9117   0.02987   0.01958  -0.0155   0.2330   1.0000
   8.250   0.9232   0.03103   0.02070  -0.0137   0.2092   1.0000
   8.500   0.9349   0.03224   0.02195  -0.0120   0.1857   1.0000
   8.750   0.9441   0.03351   0.02315  -0.0101   0.1665   1.0000
   9.000   0.9540   0.03487   0.02448  -0.0083   0.1492   1.0000
   9.250   0.9658   0.03633   0.02591  -0.0068   0.1364   1.0000
   9.500   0.9800   0.03785   0.02745  -0.0055   0.1259   1.0000
   9.750   0.9956   0.03944   0.02919  -0.0044   0.1161   1.0000
  10.000   1.0094   0.04105   0.03082  -0.0033   0.1085   1.0000
  10.250   1.0241   0.04275   0.03267  -0.0022   0.1015   1.0000
  10.500   1.0437   0.04458   0.03450  -0.0016   0.0968   1.0000
  10.750   1.0586   0.04672   0.03700  -0.0007   0.0921   1.0000
  11.000   1.0697   0.04868   0.03909   0.0004   0.0877   1.0000
  11.500   1.0861   0.05353   0.04442   0.0025   0.0810   1.0000
  11.750   1.0887   0.05651   0.04772   0.0036   0.0788   1.0000
  12.000   1.0884   0.05958   0.05106   0.0045   0.0768   1.0000
  12.250   1.0876   0.06257   0.05423   0.0052   0.0748   1.0000
  12.500   1.0964   0.06502   0.05667   0.0057   0.0721   1.0000
  12.750   1.0801   0.06931   0.06126   0.0059   0.0712   1.0000
  13.000   1.0593   0.07436   0.06662   0.0051   0.0707   1.0000
  13.250   1.0351   0.08031   0.07285   0.0032   0.0704   1.0000
  13.500   1.0079   0.08734   0.08009   0.0001   0.0704   1.0000
  13.750   0.9769   0.09584   0.08877  -0.0045   0.0707   1.0000
  14.000   0.9446   0.10586   0.09891  -0.0105   0.0713   1.0000
  14.250   0.9112   0.11764   0.11071  -0.0178   0.0718   1.0000
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