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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 200,000
Max Cl/Cd: 77.7 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3512-il-200000-n5.txt
Download as CSV file: xf-hq3512-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3417   0.10008   0.09657  -0.0464   1.0000   0.0145
 -10.000  -0.3470   0.09674   0.09329  -0.0464   1.0000   0.0143
  -9.750  -0.3549   0.09375   0.09036  -0.0458   1.0000   0.0142
  -9.500  -0.3535   0.08854   0.08520  -0.0494   0.9968   0.0142
  -9.250  -0.3487   0.08220   0.07887  -0.0554   0.9903   0.0143
  -9.000  -0.3454   0.07464   0.07133  -0.0632   0.9842   0.0146
  -8.750  -0.3462   0.06574   0.06246  -0.0731   0.9746   0.0144
  -8.500  -0.3544   0.05208   0.04860  -0.0919   0.9598   0.0141
  -8.250  -0.3616   0.04223   0.03827  -0.1000   0.9466   0.0140
  -8.000  -0.3611   0.03460   0.02997  -0.1032   0.9356   0.0143
  -7.750  -0.3459   0.02925   0.02391  -0.1051   0.9293   0.0143
  -7.500  -0.3299   0.02597   0.02009  -0.1049   0.9209   0.0146
  -7.250  -0.3052   0.02345   0.01711  -0.1055   0.9162   0.0149
  -7.000  -0.2822   0.02168   0.01500  -0.1052   0.9098   0.0153
  -6.750  -0.2569   0.02020   0.01327  -0.1052   0.9043   0.0157
  -6.500  -0.2295   0.01907   0.01201  -0.1056   0.9001   0.0165
  -6.250  -0.2057   0.01832   0.01114  -0.1051   0.8931   0.0173
  -6.000  -0.1787   0.01751   0.01020  -0.1051   0.8881   0.0184
  -5.750  -0.1528   0.01686   0.00942  -0.1049   0.8824   0.0205
  -5.500  -0.1272   0.01627   0.00880  -0.1047   0.8764   0.0228
  -5.250  -0.0994   0.01568   0.00810  -0.1047   0.8720   0.0268
  -5.000  -0.0748   0.01510   0.00749  -0.1043   0.8652   0.0318
  -4.750  -0.0477   0.01469   0.00697  -0.1042   0.8600   0.0381
  -4.500  -0.0203   0.01437   0.00661  -0.1042   0.8550   0.0446
  -4.250   0.0058   0.01412   0.00636  -0.1040   0.8486   0.0534
  -4.000   0.0339   0.01390   0.00603  -0.1041   0.8438   0.0608
  -3.750   0.0599   0.01352   0.00566  -0.1039   0.8379   0.0685
  -3.500   0.0869   0.01323   0.00530  -0.1038   0.8321   0.0764
  -3.250   0.1150   0.01290   0.00493  -0.1039   0.8276   0.0878
  -3.000   0.1408   0.01261   0.00467  -0.1036   0.8209   0.1060
  -2.750   0.1679   0.01221   0.00440  -0.1037   0.8156   0.1487
  -2.500   0.1938   0.01163   0.00417  -0.1037   0.8100   0.2537
  -2.250   0.2176   0.01087   0.00409  -0.1035   0.8037   0.4466
  -2.000   0.2441   0.01065   0.00412  -0.1030   0.7989   0.5467
  -1.750   0.2698   0.01063   0.00417  -0.1025   0.7918   0.5896
  -1.500   0.2973   0.01062   0.00413  -0.1021   0.7860   0.6211
  -1.250   0.3228   0.01065   0.00422  -0.1014   0.7790   0.6581
  -1.000   0.3488   0.01069   0.00427  -0.1006   0.7720   0.6904
  -0.750   0.3751   0.01071   0.00426  -0.1000   0.7636   0.7071
  -0.500   0.4028   0.01068   0.00414  -0.0997   0.7556   0.7162
  -0.250   0.4295   0.01068   0.00409  -0.0994   0.7456   0.7243
   0.000   0.4566   0.01067   0.00403  -0.0991   0.7370   0.7311
   0.250   0.4840   0.01067   0.00396  -0.0989   0.7282   0.7392
   0.500   0.5105   0.01068   0.00396  -0.0985   0.7192   0.7461
   0.750   0.5381   0.01070   0.00391  -0.0984   0.7105   0.7544
   1.000   0.5643   0.01070   0.00391  -0.0979   0.7002   0.7618
   1.250   0.5908   0.01073   0.00390  -0.0976   0.6894   0.7703
   1.500   0.6172   0.01075   0.00391  -0.0972   0.6799   0.7784
   1.750   0.6438   0.01078   0.00394  -0.0969   0.6705   0.7872
   2.000   0.6700   0.01082   0.00398  -0.0965   0.6600   0.7965
   2.250   0.6957   0.01086   0.00402  -0.0959   0.6489   0.8058
   2.500   0.7214   0.01090   0.00407  -0.0954   0.6372   0.8162
   3.000   0.7716   0.01100   0.00419  -0.0942   0.6107   0.8408
   3.250   0.7964   0.01105   0.00425  -0.0935   0.5949   0.8561
   3.500   0.8206   0.01110   0.00434  -0.0926   0.5764   0.8767
   3.750   0.8475   0.01115   0.00441  -0.0924   0.5559   0.9136
   4.000   0.8778   0.01131   0.00451  -0.0931   0.5308   1.0000
   4.250   0.9013   0.01160   0.00467  -0.0924   0.5033   1.0000
   4.500   0.9237   0.01195   0.00489  -0.0915   0.4741   1.0000
   4.750   0.9450   0.01236   0.00515  -0.0904   0.4438   1.0000
   5.000   0.9655   0.01282   0.00545  -0.0893   0.4139   1.0000
   5.250   0.9858   0.01329   0.00580  -0.0881   0.3860   1.0000
   5.500   1.0057   0.01379   0.00617  -0.0869   0.3599   1.0000
   5.750   1.0258   0.01427   0.00655  -0.0858   0.3369   1.0000
   6.000   1.0456   0.01477   0.00696  -0.0846   0.3174   1.0000
   6.250   1.0657   0.01525   0.00739  -0.0835   0.3022   1.0000
   6.500   1.0854   0.01574   0.00783  -0.0823   0.2893   1.0000
   6.750   1.1054   0.01621   0.00828  -0.0812   0.2783   1.0000
   7.000   1.1255   0.01668   0.00875  -0.0801   0.2682   1.0000
   7.250   1.1446   0.01718   0.00924  -0.0788   0.2591   1.0000
   7.500   1.1635   0.01766   0.00975  -0.0775   0.2495   1.0000
   7.750   1.1821   0.01811   0.01024  -0.0762   0.2407   1.0000
   8.000   1.1987   0.01864   0.01077  -0.0745   0.2326   1.0000
   8.250   1.2177   0.01907   0.01128  -0.0733   0.2245   1.0000
   8.500   1.2341   0.01962   0.01185  -0.0717   0.2169   1.0000
   8.750   1.2506   0.02014   0.01244  -0.0701   0.2055   1.0000
   9.000   1.2669   0.02068   0.01303  -0.0686   0.1935   1.0000
   9.250   1.2819   0.02129   0.01366  -0.0670   0.1802   1.0000
   9.500   1.2964   0.02196   0.01434  -0.0653   0.1670   1.0000
   9.750   1.3092   0.02275   0.01511  -0.0636   0.1516   1.0000
  10.000   1.3199   0.02369   0.01599  -0.0617   0.1346   1.0000
  10.250   1.3292   0.02479   0.01702  -0.0597   0.1147   1.0000
  10.500   1.3375   0.02600   0.01816  -0.0578   0.0978   1.0000
  10.750   1.3461   0.02724   0.01936  -0.0560   0.0844   1.0000
  11.000   1.3544   0.02854   0.02065  -0.0543   0.0721   1.0000
  11.250   1.3619   0.02994   0.02204  -0.0526   0.0607   1.0000
  11.500   1.3676   0.03152   0.02360  -0.0509   0.0490   1.0000
  11.750   1.3731   0.03317   0.02526  -0.0493   0.0384   1.0000
  12.000   1.3750   0.03518   0.02724  -0.0476   0.0268   1.0000
  12.250   1.3759   0.03735   0.02942  -0.0460   0.0194   1.0000
  12.500   1.3753   0.03974   0.03185  -0.0445   0.0143   1.0000
  12.750   1.3743   0.04224   0.03444  -0.0432   0.0117   1.0000
  13.000   1.3763   0.04454   0.03689  -0.0422   0.0103   1.0000
  13.250   1.3759   0.04717   0.03963  -0.0414   0.0091   1.0000
  13.500   1.3747   0.04997   0.04258  -0.0408   0.0086   1.0000
  13.750   1.3711   0.05318   0.04592  -0.0403   0.0082   1.0000
  14.000   1.3692   0.05633   0.04924  -0.0402   0.0079   1.0000
  14.250   1.3657   0.05981   0.05289  -0.0402   0.0076   1.0000
  14.500   1.3609   0.06362   0.05687  -0.0406   0.0073   1.0000
  14.750   1.3550   0.06776   0.06118  -0.0413   0.0071   1.0000
  15.000   1.3482   0.07221   0.06581  -0.0424   0.0070   1.0000
  15.250   1.3401   0.07707   0.07084  -0.0437   0.0069   1.0000
  15.500   1.3311   0.08227   0.07621  -0.0455   0.0068   1.0000
  15.750   1.3207   0.08792   0.08203  -0.0476   0.0067   1.0000
  16.000   1.3096   0.09392   0.08820  -0.0501   0.0066   1.0000
  16.250   1.2981   0.10017   0.09462  -0.0529   0.0065   1.0000
  16.500   1.2858   0.10675   0.10136  -0.0559   0.0064   1.0000
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