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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 50,000
Max Cl/Cd: 36.13 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3011-il-50000.txt
Download as CSV file: xf-hq3011-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3450   0.10170   0.09514  -0.0274   1.0000   0.2673
  -8.250  -0.3442   0.09923   0.09276  -0.0260   1.0000   0.2820
  -8.000  -0.3442   0.09679   0.09041  -0.0243   1.0000   0.2972
  -7.750  -0.3449   0.09448   0.08819  -0.0224   1.0000   0.3124
  -7.500  -0.3474   0.09235   0.08617  -0.0201   1.0000   0.3282
  -7.250  -0.3539   0.09059   0.08452  -0.0174   1.0000   0.3446
  -7.000  -0.3660   0.08935   0.08342  -0.0140   1.0000   0.3607
  -6.750  -0.3802   0.08832   0.08252  -0.0100   1.0000   0.3759
  -6.500  -0.3608   0.08446   0.07867  -0.0076   1.0000   0.3983
  -6.250  -0.3750   0.08357   0.07790  -0.0031   1.0000   0.4176
  -6.000  -0.4023   0.08357   0.07807   0.0026   1.0000   0.4341
  -5.750  -0.4010   0.08158   0.07614   0.0069   1.0000   0.4630
  -4.750  -0.4233   0.04661   0.03878  -0.0443   1.0000   0.1300
  -4.500  -0.4029   0.04277   0.03480  -0.0443   1.0000   0.1263
  -4.250  -0.3784   0.03948   0.03095  -0.0449   1.0000   0.1259
  -4.000  -0.3518   0.03679   0.02751  -0.0453   1.0000   0.1292
  -3.750  -0.3268   0.03412   0.02455  -0.0452   1.0000   0.1332
  -3.500  -0.3014   0.03242   0.02231  -0.0449   1.0000   0.1446
  -3.250  -0.2778   0.03059   0.02038  -0.0444   1.0000   0.1575
  -3.000  -0.2538   0.02913   0.01870  -0.0436   1.0000   0.1734
  -2.750  -0.2317   0.02781   0.01751  -0.0427   1.0000   0.1935
  -2.500  -0.2091   0.02679   0.01641  -0.0415   1.0000   0.2159
  -2.250  -0.1855   0.02569   0.01554  -0.0409   1.0000   0.2559
  -2.000  -0.1628   0.02321   0.01526  -0.0394   1.0000   0.5671
  -1.750  -0.1758   0.02300   0.01584  -0.0275   1.0000   0.7985
  -1.500  -0.1583   0.02244   0.01534  -0.0230   1.0000   0.9837
  -1.250  -0.1347   0.02258   0.01500  -0.0244   1.0000   1.0000
  -1.000  -0.1102   0.02287   0.01487  -0.0258   1.0000   1.0000
  -0.750  -0.0858   0.02325   0.01488  -0.0270   1.0000   1.0000
  -0.500  -0.0620   0.02370   0.01500  -0.0281   1.0000   1.0000
  -0.250  -0.0390   0.02421   0.01520  -0.0289   1.0000   1.0000
   0.000  -0.0167   0.02477   0.01551  -0.0295   1.0000   1.0000
   0.250   0.0049   0.02538   0.01590  -0.0301   1.0000   1.0000
   0.500   0.0260   0.02605   0.01635  -0.0305   1.0000   1.0000
   0.750   0.0466   0.02676   0.01688  -0.0309   1.0000   1.0000
   1.000   0.0713   0.02764   0.01761  -0.0322   0.9976   1.0000
   1.250   0.1208   0.02931   0.01908  -0.0379   0.9838   1.0000
   1.500   0.1673   0.03084   0.02045  -0.0430   0.9696   1.0000
   1.750   0.2101   0.03219   0.02168  -0.0473   0.9547   1.0000
   2.000   0.2483   0.03332   0.02273  -0.0506   0.9383   1.0000
   2.250   0.2865   0.03442   0.02378  -0.0537   0.9209   1.0000
   2.500   0.3274   0.03551   0.02484  -0.0570   0.9028   1.0000
   2.750   0.3730   0.03660   0.02592  -0.0609   0.8849   1.0000
   3.000   0.4066   0.03747   0.02679  -0.0626   0.8658   1.0000
   3.250   0.4419   0.03830   0.02765  -0.0645   0.8469   1.0000
   3.500   0.4840   0.03904   0.02846  -0.0671   0.8286   1.0000
   3.750   0.5205   0.03970   0.02918  -0.0687   0.8098   1.0000
   4.000   0.5524   0.04029   0.02985  -0.0695   0.7895   1.0000
   4.250   0.5991   0.04046   0.03017  -0.0718   0.7708   1.0000
   4.500   0.6285   0.04087   0.03067  -0.0718   0.7492   1.0000
   4.750   0.6742   0.04057   0.03053  -0.0732   0.7293   1.0000
   5.000   0.7129   0.04027   0.03042  -0.0734   0.7080   1.0000
   5.250   0.7608   0.03923   0.02959  -0.0741   0.6875   1.0000
   5.500   0.8260   0.03685   0.02751  -0.0756   0.6700   1.0000
   5.750   0.8573   0.03621   0.02704  -0.0742   0.6456   1.0000
   6.000   0.9089   0.03416   0.02520  -0.0740   0.6232   1.0000
   6.250   0.9638   0.03182   0.02305  -0.0740   0.5982   1.0000
   6.500   0.9992   0.03087   0.02219  -0.0727   0.5680   1.0000
   6.750   1.0295   0.03043   0.02179  -0.0711   0.5357   1.0000
   7.000   1.0604   0.03020   0.02156  -0.0697   0.5030   1.0000
   7.250   1.0917   0.03022   0.02145  -0.0685   0.4700   1.0000
   7.500   1.1143   0.03097   0.02214  -0.0669   0.4383   1.0000
   7.750   1.1357   0.03194   0.02307  -0.0652   0.4079   1.0000
   8.000   1.1561   0.03302   0.02410  -0.0636   0.3783   1.0000
   8.250   1.1756   0.03421   0.02528  -0.0619   0.3497   1.0000
   8.500   1.1945   0.03552   0.02654  -0.0602   0.3221   1.0000
   8.750   1.2129   0.03695   0.02788  -0.0585   0.2949   1.0000
   9.000   1.2320   0.03853   0.02933  -0.0570   0.2684   1.0000
   9.250   1.2423   0.04056   0.03158  -0.0546   0.2460   1.0000
   9.500   1.2590   0.04247   0.03343  -0.0530   0.2239   1.0000
   9.750   1.2694   0.04479   0.03595  -0.0508   0.2061   1.0000
  10.000   1.2817   0.04739   0.03878  -0.0489   0.1912   1.0000
  10.250   1.2912   0.04986   0.04143  -0.0468   0.1776   1.0000
  10.500   1.3007   0.05271   0.04446  -0.0448   0.1666   1.0000
  10.750   1.3178   0.05578   0.04756  -0.0438   0.1562   1.0000
  11.000   1.3016   0.05951   0.05190  -0.0398   0.1522   1.0000
  11.250   1.3135   0.06218   0.05457  -0.0384   0.1419   1.0000
  11.500   1.2915   0.06626   0.05911  -0.0346   0.1402   1.0000
  11.750   1.2668   0.07032   0.06348  -0.0311   0.1396   1.0000
  12.000   1.2388   0.07489   0.06830  -0.0285   0.1397   1.0000
  12.250   1.2086   0.08016   0.07378  -0.0274   0.1403   1.0000
  12.500   1.1777   0.08631   0.08008  -0.0276   0.1413   1.0000
  12.750   1.1474   0.09341   0.08728  -0.0292   0.1424   1.0000
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