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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.22 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-1000000-n5.txt
Download as CSV file: xf-hq2090sm-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5014   0.10807   0.10639  -0.0165   1.0000   0.0028
 -10.750  -0.5016   0.10356   0.10189  -0.0184   1.0000   0.0026
  -9.750  -0.7533   0.03130   0.02896  -0.0562   1.0000   0.0025
  -9.500  -0.7421   0.02646   0.02369  -0.0574   0.9953   0.0026
  -9.250  -0.7208   0.02273   0.01951  -0.0591   0.9897   0.0027
  -9.000  -0.6934   0.02068   0.01719  -0.0607   0.9861   0.0028
  -8.750  -0.6670   0.01872   0.01494  -0.0618   0.9807   0.0029
  -8.500  -0.6378   0.01726   0.01325  -0.0630   0.9765   0.0030
  -8.250  -0.6103   0.01609   0.01189  -0.0636   0.9701   0.0031
  -8.000  -0.5821   0.01505   0.01065  -0.0643   0.9642   0.0032
  -7.750  -0.5558   0.01416   0.00960  -0.0644   0.9564   0.0033
  -7.500  -0.5297   0.01344   0.00875  -0.0644   0.9489   0.0034
  -7.250  -0.5044   0.01270   0.00785  -0.0641   0.9402   0.0035
  -7.000  -0.4788   0.01219   0.00725  -0.0638   0.9313   0.0036
  -6.750  -0.4542   0.01143   0.00634  -0.0634   0.9221   0.0038
  -6.500  -0.4292   0.01079   0.00557  -0.0629   0.9120   0.0043
  -6.250  -0.4033   0.01035   0.00503  -0.0626   0.9017   0.0046
  -6.000  -0.3773   0.00996   0.00456  -0.0623   0.8916   0.0050
  -5.750  -0.3511   0.00963   0.00413  -0.0620   0.8818   0.0054
  -5.500  -0.3245   0.00933   0.00374  -0.0618   0.8720   0.0059
  -5.250  -0.2977   0.00907   0.00340  -0.0616   0.8632   0.0062
  -5.000  -0.2709   0.00878   0.00302  -0.0614   0.8547   0.0072
  -4.750  -0.2438   0.00851   0.00273  -0.0613   0.8464   0.0093
  -4.500  -0.2167   0.00828   0.00248  -0.0611   0.8386   0.0135
  -4.250  -0.1894   0.00810   0.00228  -0.0611   0.8307   0.0184
  -4.000  -0.1619   0.00794   0.00211  -0.0610   0.8232   0.0224
  -3.750  -0.1343   0.00782   0.00195  -0.0610   0.8153   0.0244
  -3.500  -0.1067   0.00766   0.00177  -0.0609   0.8078   0.0307
  -3.250  -0.0792   0.00754   0.00162  -0.0609   0.7990   0.0385
  -3.000  -0.0516   0.00740   0.00148  -0.0608   0.7886   0.0481
  -2.750  -0.0241   0.00728   0.00135  -0.0608   0.7783   0.0590
  -2.500   0.0035   0.00717   0.00124  -0.0607   0.7696   0.0741
  -2.250   0.0313   0.00701   0.00113  -0.0607   0.7618   0.0972
  -2.000   0.0589   0.00683   0.00103  -0.0608   0.7546   0.1326
  -1.750   0.0863   0.00658   0.00093  -0.0608   0.7461   0.1911
  -1.500   0.1135   0.00631   0.00084  -0.0608   0.7357   0.2611
  -1.250   0.1397   0.00580   0.00074  -0.0609   0.7240   0.4073
  -1.000   0.1667   0.00559   0.00070  -0.0608   0.7115   0.4844
  -0.750   0.1942   0.00553   0.00067  -0.0608   0.6985   0.5160
  -0.500   0.2215   0.00541   0.00067  -0.0607   0.6868   0.5711
  -0.250   0.2490   0.00533   0.00069  -0.0606   0.6759   0.6163
   0.000   0.2764   0.00529   0.00073  -0.0605   0.6639   0.6570
   0.250   0.3037   0.00532   0.00075  -0.0603   0.6467   0.6809
   0.500   0.3311   0.00539   0.00077  -0.0602   0.6258   0.6909
   0.750   0.3586   0.00548   0.00079  -0.0601   0.6036   0.6989
   1.000   0.3859   0.00558   0.00083  -0.0600   0.5805   0.7067
   1.250   0.4130   0.00571   0.00088  -0.0599   0.5543   0.7141
   1.500   0.4399   0.00587   0.00095  -0.0597   0.5229   0.7218
   1.750   0.4667   0.00604   0.00102  -0.0595   0.4921   0.7290
   2.000   0.4932   0.00625   0.00113  -0.0593   0.4586   0.7367
   2.250   0.5198   0.00644   0.00123  -0.0592   0.4280   0.7441
   2.500   0.5462   0.00666   0.00135  -0.0590   0.3940   0.7522
   2.750   0.5716   0.00700   0.00150  -0.0586   0.3422   0.7603
   3.250   0.6232   0.00757   0.00183  -0.0581   0.2669   0.7794
   3.500   0.6489   0.00785   0.00200  -0.0578   0.2344   0.7900
   3.750   0.6746   0.00810   0.00218  -0.0575   0.2043   0.8024
   4.000   0.7001   0.00834   0.00238  -0.0572   0.1786   0.8173
   4.250   0.7252   0.00858   0.00258  -0.0568   0.1538   0.8370
   4.500   0.7498   0.00876   0.00278  -0.0562   0.1349   0.8655
   4.750   0.7720   0.00887   0.00298  -0.0550   0.1148   0.9257
   5.000   0.8042   0.00922   0.00325  -0.0562   0.0873   1.0000
   5.250   0.8288   0.00968   0.00358  -0.0558   0.0616   1.0000
   5.500   0.8544   0.00999   0.00385  -0.0555   0.0508   1.0000
   5.750   0.8801   0.01030   0.00412  -0.0553   0.0415   1.0000
   6.000   0.9055   0.01063   0.00441  -0.0550   0.0326   1.0000
   6.250   0.9309   0.01095   0.00471  -0.0547   0.0274   1.0000
   6.500   0.9565   0.01124   0.00503  -0.0544   0.0233   1.0000
   6.750   0.9811   0.01164   0.00538  -0.0540   0.0173   1.0000
   7.000   1.0051   0.01211   0.00580  -0.0535   0.0098   1.0000
   7.250   1.0294   0.01256   0.00624  -0.0530   0.0065   1.0000
   7.500   1.0539   0.01295   0.00667  -0.0526   0.0057   1.0000
   7.750   1.0779   0.01338   0.00714  -0.0521   0.0050   1.0000
   8.000   1.1013   0.01389   0.00768  -0.0515   0.0043   1.0000
   8.250   1.1237   0.01452   0.00842  -0.0507   0.0038   1.0000
   8.500   1.1473   0.01496   0.00892  -0.0501   0.0036   1.0000
   8.750   1.1704   0.01544   0.00945  -0.0495   0.0034   1.0000
   9.000   1.1929   0.01597   0.01004  -0.0489   0.0031   1.0000
   9.250   1.2150   0.01653   0.01066  -0.0481   0.0029   1.0000
   9.500   1.2366   0.01712   0.01130  -0.0474   0.0026   1.0000
   9.750   1.2575   0.01775   0.01200  -0.0465   0.0025   1.0000
  10.000   1.2772   0.01849   0.01281  -0.0455   0.0023   1.0000
  10.250   1.2951   0.01941   0.01386  -0.0442   0.0022   1.0000
  10.500   1.3088   0.02071   0.01530  -0.0424   0.0020   1.0000
  10.750   1.3269   0.02146   0.01614  -0.0412   0.0020   1.0000
  11.000   1.3423   0.02240   0.01719  -0.0397   0.0019   1.0000
  11.250   1.3583   0.02322   0.01810  -0.0382   0.0019   1.0000
  11.500   1.3727   0.02406   0.01904  -0.0366   0.0018   1.0000
  11.750   1.3815   0.02507   0.02016  -0.0341   0.0018   1.0000
  12.000   1.3893   0.02609   0.02129  -0.0315   0.0017   1.0000
  12.250   1.3943   0.02733   0.02265  -0.0289   0.0017   1.0000
  12.500   1.3986   0.02868   0.02413  -0.0264   0.0017   1.0000
  12.750   1.4014   0.03021   0.02579  -0.0241   0.0016   1.0000
  13.000   1.4072   0.03158   0.02726  -0.0224   0.0015   1.0000
  13.250   1.3993   0.03422   0.03012  -0.0200   0.0016   1.0000
  13.500   1.4063   0.03565   0.03163  -0.0189   0.0015   1.0000
  13.750   1.4062   0.03788   0.03398  -0.0178   0.0014   1.0000
  14.000   1.3980   0.04107   0.03735  -0.0168   0.0014   1.0000
  14.250   1.3946   0.04399   0.04040  -0.0165   0.0014   1.0000
  14.500   1.3894   0.04734   0.04388  -0.0166   0.0014   1.0000
  14.750   1.3779   0.05175   0.04846  -0.0174   0.0014   1.0000
  15.000   1.3644   0.05687   0.05375  -0.0190   0.0014   1.0000
  15.250   1.3491   0.06277   0.05981  -0.0216   0.0014   1.0000
  15.500   1.3368   0.06874   0.06591  -0.0246   0.0013   1.0000
  15.750   1.3157   0.07695   0.07430  -0.0293   0.0013   1.0000
  16.000   1.2830   0.08827   0.08583  -0.0360   0.0014   1.0000
  16.250   1.2612   0.09795   0.09565  -0.0417   0.0014   1.0000
  16.500   1.2294   0.11012   0.10798  -0.0487   0.0014   1.0000
  16.750   1.1919   0.12397   0.12199  -0.0566   0.0015   1.0000
  17.000   1.1589   0.13718   0.13532  -0.0641   0.0015   1.0000
  17.250   1.1243   0.15152   0.14978  -0.0723   0.0016   1.0000
  17.500   1.0994   0.16395   0.16230  -0.0793   0.0016   1.0000
  17.750   1.0686   0.17910   0.17755  -0.0877   0.0017   1.0000
  18.000   1.0306   0.19855   0.19710  -0.0980   0.0018   1.0000
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