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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 200,000
Max Cl/Cd: 68.43 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1510-il-200000.txt
Download as CSV file: xf-hq1510-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5123   0.08911   0.08567  -0.0329   1.0000   0.0524
  -9.250  -0.5272   0.08208   0.07868  -0.0407   1.0000   0.0526
  -9.000  -0.5442   0.07759   0.07416  -0.0444   1.0000   0.0527
  -8.750  -0.5606   0.07397   0.07045  -0.0458   1.0000   0.0528
  -8.500  -0.5712   0.07037   0.06670  -0.0466   1.0000   0.0529
  -8.250  -0.5857   0.06275   0.05902  -0.0477   1.0000   0.0538
  -8.000  -0.5753   0.05866   0.05504  -0.0471   1.0000   0.0549
  -7.750  -0.5708   0.05551   0.05186  -0.0464   1.0000   0.0557
  -7.500  -0.5672   0.05245   0.04875  -0.0454   1.0000   0.0570
  -7.250  -0.5648   0.04937   0.04554  -0.0441   1.0000   0.0584
  -7.000  -0.5859   0.03540   0.03022  -0.0392   1.0000   0.0289
  -6.750  -0.5826   0.03182   0.02630  -0.0364   1.0000   0.0282
  -6.500  -0.5753   0.02881   0.02290  -0.0337   1.0000   0.0280
  -6.250  -0.5644   0.02626   0.01996  -0.0313   1.0000   0.0281
  -6.000  -0.5501   0.02421   0.01755  -0.0292   1.0000   0.0287
  -5.750  -0.5340   0.02304   0.01606  -0.0273   1.0000   0.0302
  -5.500  -0.5144   0.02075   0.01365  -0.0267   0.9994   0.0334
  -5.250  -0.4778   0.01920   0.01189  -0.0285   0.9956   0.0364
  -5.000  -0.4420   0.01771   0.01019  -0.0300   0.9917   0.0418
  -4.750  -0.4055   0.01684   0.00928  -0.0321   0.9868   0.0527
  -4.500  -0.3691   0.01553   0.00801  -0.0343   0.9829   0.0682
  -4.250  -0.3353   0.01481   0.00733  -0.0359   0.9771   0.0845
  -4.000  -0.2984   0.01418   0.00670  -0.0382   0.9721   0.1047
  -3.750  -0.2602   0.01324   0.00597  -0.0408   0.9684   0.1413
  -3.500  -0.2334   0.01174   0.00541  -0.0418   0.9610   0.3229
  -3.250  -0.2003   0.01085   0.00539  -0.0432   0.9566   0.5464
  -3.000  -0.1678   0.01075   0.00541  -0.0439   0.9502   0.6197
  -2.750  -0.1318   0.01072   0.00543  -0.0452   0.9449   0.6669
  -2.500  -0.0932   0.01072   0.00542  -0.0470   0.9413   0.7025
  -2.250  -0.0644   0.01074   0.00541  -0.0469   0.9332   0.7263
  -2.000  -0.0294   0.01072   0.00540  -0.0477   0.9283   0.7505
  -1.750  -0.0021   0.01076   0.00544  -0.0470   0.9204   0.7750
  -1.500   0.0292   0.01071   0.00540  -0.0471   0.9145   0.7952
  -1.250   0.0562   0.01067   0.00533  -0.0465   0.9061   0.8096
  -1.000   0.0857   0.01059   0.00523  -0.0463   0.8998   0.8256
  -0.750   0.1094   0.01055   0.00521  -0.0450   0.8906   0.8426
  -0.500   0.1368   0.01045   0.00509  -0.0442   0.8842   0.8576
  -0.250   0.1606   0.01038   0.00502  -0.0430   0.8740   0.8709
   0.000   0.1857   0.01027   0.00491  -0.0420   0.8639   0.8836
   0.250   0.2116   0.01013   0.00475  -0.0409   0.8540   0.8963
   0.500   0.2376   0.01001   0.00462  -0.0400   0.8434   0.9098
   0.750   0.2653   0.00994   0.00454  -0.0395   0.8322   0.9240
   1.000   0.2969   0.00986   0.00446  -0.0398   0.8212   0.9385
   1.250   0.3333   0.00978   0.00437  -0.0413   0.8110   0.9520
   1.500   0.3732   0.00972   0.00430  -0.0436   0.8008   0.9644
   1.750   0.4148   0.00967   0.00426  -0.0464   0.7894   0.9764
   2.000   0.4578   0.00961   0.00422  -0.0496   0.7773   0.9878
   2.250   0.4984   0.00955   0.00415  -0.0524   0.7644   1.0000
   2.500   0.5140   0.00954   0.00412  -0.0503   0.7510   1.0000
   2.750   0.5342   0.00957   0.00412  -0.0489   0.7367   1.0000
   3.000   0.5573   0.00961   0.00415  -0.0479   0.7212   1.0000
   3.250   0.5816   0.00965   0.00416  -0.0471   0.7040   1.0000
   3.500   0.6062   0.00970   0.00418  -0.0462   0.6842   1.0000
   3.750   0.6307   0.00976   0.00420  -0.0453   0.6600   1.0000
   4.000   0.6548   0.00985   0.00425  -0.0443   0.6298   1.0000
   4.250   0.6781   0.00999   0.00430  -0.0432   0.5902   1.0000
   4.500   0.7007   0.01024   0.00439  -0.0420   0.5399   1.0000
   4.750   0.7219   0.01067   0.00455  -0.0407   0.4797   1.0000
   5.000   0.7423   0.01124   0.00483  -0.0394   0.4176   1.0000
   5.250   0.7628   0.01188   0.00522  -0.0382   0.3619   1.0000
   5.500   0.7842   0.01248   0.00564  -0.0373   0.3189   1.0000
   5.750   0.8058   0.01308   0.00610  -0.0364   0.2833   1.0000
   6.000   0.8273   0.01372   0.00659  -0.0356   0.2490   1.0000
   6.250   0.8487   0.01435   0.00710  -0.0347   0.2082   1.0000
   6.500   0.8680   0.01523   0.00772  -0.0336   0.1474   1.0000
   6.750   0.8852   0.01643   0.00862  -0.0322   0.1075   1.0000
   7.000   0.9036   0.01749   0.00957  -0.0309   0.0899   1.0000
   7.250   0.9229   0.01847   0.01056  -0.0296   0.0799   1.0000
   7.500   0.9406   0.01972   0.01177  -0.0282   0.0731   1.0000
   7.750   0.9616   0.02063   0.01278  -0.0272   0.0675   1.0000
   8.000   0.9799   0.02215   0.01425  -0.0260   0.0615   1.0000
   8.250   1.0016   0.02261   0.01489  -0.0252   0.0554   1.0000
   8.500   1.0195   0.02386   0.01611  -0.0242   0.0489   1.0000
   8.750   1.0397   0.02442   0.01687  -0.0232   0.0435   1.0000
   9.000   1.0557   0.02628   0.01873  -0.0219   0.0377   1.0000
   9.250   1.0723   0.02681   0.01944  -0.0205   0.0309   1.0000
   9.500   1.0857   0.02861   0.02137  -0.0188   0.0252   1.0000
   9.750   1.1004   0.02996   0.02284  -0.0172   0.0221   1.0000
  10.000   1.1122   0.03232   0.02528  -0.0157   0.0202   1.0000
  10.250   1.1227   0.03548   0.02880  -0.0139   0.0191   1.0000
  10.500   1.1313   0.03790   0.03155  -0.0118   0.0184   1.0000
  10.750   1.1339   0.04060   0.03457  -0.0092   0.0180   1.0000
  11.000   1.1312   0.04343   0.03771  -0.0063   0.0177   1.0000
  11.250   1.1232   0.04656   0.04116  -0.0035   0.0176   1.0000
  11.500   1.1122   0.04993   0.04482  -0.0013   0.0176   1.0000
  11.750   1.0974   0.05371   0.04887   0.0002   0.0176   1.0000
  12.000   1.0805   0.05790   0.05333   0.0008   0.0176   1.0000
  12.250   1.0613   0.06270   0.05838   0.0004   0.0176   1.0000
  12.500   1.0422   0.06797   0.06386  -0.0012   0.0178   1.0000
  12.750   1.0198   0.07431   0.07040  -0.0042   0.0179   1.0000
  13.000   0.9981   0.08133   0.07760  -0.0084   0.0181   1.0000
  13.250   0.9767   0.08922   0.08564  -0.0136   0.0184   1.0000
  13.500   0.9498   0.09953   0.09610  -0.0208   0.0186   1.0000
  13.750   0.9266   0.11002   0.10668  -0.0278   0.0191   1.0000
  14.000   0.8992   0.12259   0.11926  -0.0353   0.0196   1.0000
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