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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 200,000
Max Cl/Cd: 67.84 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1511-il-200000.txt
Download as CSV file: xf-hq1511-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6361   0.05343   0.04915  -0.0503   1.0000   0.0359
  -8.500  -0.6720   0.04181   0.03683  -0.0473   1.0000   0.0283
  -8.250  -0.6653   0.03912   0.03395  -0.0453   1.0000   0.0276
  -8.000  -0.6652   0.03551   0.03007  -0.0426   1.0000   0.0272
  -7.750  -0.6631   0.03264   0.02691  -0.0395   1.0000   0.0269
  -7.500  -0.6595   0.03007   0.02402  -0.0364   1.0000   0.0268
  -7.250  -0.6529   0.02779   0.02140  -0.0335   1.0000   0.0268
  -7.000  -0.6428   0.02581   0.01911  -0.0310   1.0000   0.0271
  -6.750  -0.6300   0.02417   0.01717  -0.0287   1.0000   0.0276
  -6.500  -0.6018   0.02172   0.01448  -0.0295   0.9973   0.0290
  -6.250  -0.5657   0.02042   0.01313  -0.0317   0.9933   0.0317
  -6.000  -0.5313   0.01885   0.01141  -0.0333   0.9885   0.0376
  -5.750  -0.4935   0.01806   0.01062  -0.0359   0.9842   0.0497
  -5.500  -0.4587   0.01745   0.00994  -0.0377   0.9788   0.0602
  -5.250  -0.4215   0.01706   0.00946  -0.0400   0.9739   0.0692
  -5.000  -0.3834   0.01614   0.00859  -0.0426   0.9705   0.0781
  -4.750  -0.3518   0.01547   0.00791  -0.0437   0.9638   0.0877
  -4.500  -0.3153   0.01476   0.00722  -0.0459   0.9594   0.1020
  -4.250  -0.2760   0.01395   0.00649  -0.0487   0.9566   0.1264
  -4.000  -0.2492   0.01282   0.00595  -0.0494   0.9489   0.2254
  -3.750  -0.2194   0.01146   0.00559  -0.0508   0.9440   0.4474
  -3.500  -0.1909   0.01112   0.00566  -0.0508   0.9378   0.5578
  -3.250  -0.1592   0.01108   0.00567  -0.0513   0.9314   0.6137
  -3.000  -0.1231   0.01106   0.00567  -0.0524   0.9271   0.6510
  -2.750  -0.0974   0.01111   0.00569  -0.0516   0.9177   0.6773
  -2.500  -0.0649   0.01112   0.00566  -0.0519   0.9126   0.7036
  -2.250  -0.0404   0.01117   0.00573  -0.0506   0.9032   0.7235
  -2.000  -0.0111   0.01117   0.00570  -0.0501   0.8974   0.7448
  -1.750   0.0126   0.01122   0.00574  -0.0488   0.8880   0.7628
  -1.500   0.0407   0.01117   0.00565  -0.0483   0.8821   0.7747
  -1.250   0.0654   0.01116   0.00562  -0.0473   0.8732   0.7857
  -1.000   0.0923   0.01111   0.00554  -0.0466   0.8668   0.7979
  -0.750   0.1163   0.01111   0.00553  -0.0454   0.8577   0.8113
  -0.500   0.1418   0.01107   0.00546  -0.0445   0.8501   0.8237
  -0.250   0.1667   0.01103   0.00542  -0.0435   0.8418   0.8347
   0.000   0.1917   0.01098   0.00537  -0.0425   0.8337   0.8450
   0.250   0.2172   0.01090   0.00527  -0.0417   0.8253   0.8555
   0.500   0.2416   0.01084   0.00521  -0.0406   0.8153   0.8672
   0.750   0.2666   0.01074   0.00511  -0.0395   0.8070   0.8782
   1.000   0.2910   0.01066   0.00506  -0.0384   0.7973   0.8895
   1.250   0.3163   0.01059   0.00500  -0.0376   0.7881   0.9012
   1.500   0.3431   0.01049   0.00489  -0.0369   0.7793   0.9131
   1.750   0.3698   0.01042   0.00485  -0.0364   0.7684   0.9264
   2.000   0.4010   0.01035   0.00481  -0.0368   0.7582   0.9387
   2.250   0.4366   0.01028   0.00472  -0.0381   0.7482   0.9506
   2.500   0.4755   0.01023   0.00471  -0.0402   0.7363   0.9627
   2.750   0.5168   0.01019   0.00471  -0.0429   0.7233   0.9747
   3.000   0.5595   0.01015   0.00468  -0.0460   0.7092   0.9860
   3.250   0.6021   0.01009   0.00464  -0.0491   0.6927   0.9982
   3.500   0.6198   0.01008   0.00461  -0.0475   0.6761   1.0000
   3.750   0.6377   0.01009   0.00459  -0.0457   0.6532   1.0000
   4.000   0.6595   0.01012   0.00454  -0.0445   0.6234   1.0000
   4.250   0.6825   0.01022   0.00456  -0.0434   0.5901   1.0000
   4.500   0.7055   0.01040   0.00462  -0.0424   0.5496   1.0000
   4.750   0.7271   0.01074   0.00473  -0.0412   0.5002   1.0000
   5.000   0.7477   0.01124   0.00497  -0.0399   0.4499   1.0000
   5.250   0.7687   0.01180   0.00533  -0.0388   0.4037   1.0000
   5.500   0.7902   0.01232   0.00568  -0.0378   0.3625   1.0000
   5.750   0.8119   0.01286   0.00606  -0.0369   0.3297   1.0000
   6.000   0.8332   0.01344   0.00650  -0.0360   0.3023   1.0000
   6.250   0.8545   0.01404   0.00698  -0.0351   0.2768   1.0000
   6.500   0.8765   0.01455   0.00744  -0.0344   0.2509   1.0000
   6.750   0.8981   0.01507   0.00792  -0.0336   0.2234   1.0000
   7.000   0.9189   0.01566   0.00841  -0.0326   0.1899   1.0000
   7.250   0.9386   0.01637   0.00893  -0.0316   0.1426   1.0000
   7.500   0.9545   0.01749   0.00981  -0.0301   0.1108   1.0000
   7.750   0.9704   0.01863   0.01084  -0.0285   0.0877   1.0000
   8.000   0.9856   0.01981   0.01194  -0.0268   0.0720   1.0000
   8.250   1.0011   0.02097   0.01310  -0.0251   0.0619   1.0000
   8.500   1.0152   0.02229   0.01438  -0.0234   0.0553   1.0000
   8.750   1.0328   0.02325   0.01544  -0.0220   0.0503   1.0000
   9.000   1.0470   0.02485   0.01698  -0.0203   0.0465   1.0000
   9.250   1.0652   0.02620   0.01845  -0.0191   0.0440   1.0000
   9.500   1.0833   0.02735   0.01972  -0.0178   0.0412   1.0000
   9.750   1.1000   0.02855   0.02095  -0.0166   0.0386   1.0000
  10.000   1.1213   0.03126   0.02369  -0.0163   0.0365   1.0000
  10.250   1.1393   0.03317   0.02585  -0.0152   0.0354   1.0000
  10.500   1.1539   0.03474   0.02766  -0.0136   0.0340   1.0000
  10.750   1.1664   0.03640   0.02954  -0.0120   0.0325   1.0000
  11.000   1.1766   0.03811   0.03142  -0.0102   0.0312   1.0000
  11.250   1.1846   0.04020   0.03370  -0.0083   0.0304   1.0000
  11.500   1.1905   0.04243   0.03610  -0.0063   0.0297   1.0000
  11.750   1.1935   0.04511   0.03897  -0.0043   0.0292   1.0000
  12.000   1.1918   0.04853   0.04260  -0.0024   0.0286   1.0000
  12.250   1.1820   0.05245   0.04680  -0.0003   0.0283   1.0000
  12.750   1.1463   0.06069   0.05558   0.0028   0.0279   1.0000
  13.000   1.1288   0.06468   0.05980   0.0032   0.0279   1.0000
  13.250   1.1108   0.06850   0.06384   0.0028   0.0277   1.0000
  13.500   1.0898   0.07473   0.07027   0.0014   0.0280   1.0000
  13.750   1.0684   0.07985   0.07560  -0.0011   0.0279   1.0000
  14.250   0.8428   0.14562   0.14219  -0.0434   0.0415   1.0000
  14.500   0.8518   0.14900   0.14560  -0.0432   0.0470   1.0000
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