Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8064 (s8064-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 200,000
Max Cl/Cd: 55.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8064-il-200000-n5.txt
Download as CSV file: xf-s8064-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5976   0.08891   0.08531  -0.0460   1.0000   0.0094
 -12.500  -0.6262   0.07646   0.07277  -0.0543   1.0000   0.0092
 -12.250  -0.6423   0.06874   0.06496  -0.0601   1.0000   0.0091
 -12.000  -0.6674   0.06081   0.05685  -0.0659   1.0000   0.0090
 -11.750  -0.6898   0.05491   0.05075  -0.0692   1.0000   0.0090
 -11.500  -0.7064   0.05075   0.04641  -0.0703   1.0000   0.0090
 -11.250  -0.7254   0.04721   0.04268  -0.0697   1.0000   0.0090
 -11.000  -0.7396   0.04458   0.03987  -0.0682   0.9957   0.0089
 -10.750  -0.7444   0.04065   0.03554  -0.0691   0.9848   0.0090
 -10.500  -0.7428   0.03746   0.03196  -0.0690   0.9771   0.0090
 -10.250  -0.7349   0.03470   0.02881  -0.0688   0.9721   0.0091
 -10.000  -0.7270   0.03228   0.02601  -0.0675   0.9666   0.0093
  -9.750  -0.7125   0.03037   0.02378  -0.0669   0.9626   0.0094
  -9.500  -0.6955   0.02834   0.02150  -0.0665   0.9594   0.0096
  -9.250  -0.6791   0.02689   0.01990  -0.0658   0.9557   0.0100
  -9.000  -0.6618   0.02573   0.01859  -0.0649   0.9521   0.0102
  -8.750  -0.6424   0.02482   0.01756  -0.0643   0.9488   0.0111
  -8.500  -0.6212   0.02385   0.01642  -0.0639   0.9461   0.0119
  -8.250  -0.6011   0.02283   0.01521  -0.0631   0.9434   0.0126
  -8.000  -0.5855   0.02183   0.01411  -0.0615   0.9394   0.0130
  -7.750  -0.5683   0.02091   0.01312  -0.0602   0.9358   0.0136
  -7.500  -0.5487   0.02014   0.01224  -0.0592   0.9329   0.0144
  -7.250  -0.5283   0.01940   0.01138  -0.0582   0.9304   0.0158
  -7.000  -0.5109   0.01880   0.01067  -0.0567   0.9267   0.0172
  -6.750  -0.4928   0.01813   0.00996  -0.0553   0.9231   0.0204
  -6.500  -0.4730   0.01752   0.00932  -0.0541   0.9201   0.0264
  -6.250  -0.4516   0.01698   0.00877  -0.0533   0.9176   0.0379
  -6.000  -0.4307   0.01653   0.00834  -0.0523   0.9148   0.0511
  -5.750  -0.4121   0.01610   0.00801  -0.0510   0.9109   0.0711
  -5.500  -0.3918   0.01564   0.00766  -0.0500   0.9075   0.0953
  -5.250  -0.3701   0.01521   0.00728  -0.0491   0.9047   0.1208
  -5.000  -0.3480   0.01476   0.00692  -0.0483   0.9024   0.1554
  -4.750  -0.3298   0.01433   0.00667  -0.0469   0.8984   0.1992
  -4.500  -0.3119   0.01383   0.00640  -0.0455   0.8943   0.2591
  -4.250  -0.2934   0.01327   0.00614  -0.0440   0.8910   0.3345
  -4.000  -0.2742   0.01273   0.00590  -0.0426   0.8884   0.4176
  -3.750  -0.2561   0.01239   0.00581  -0.0409   0.8844   0.4867
  -3.500  -0.2364   0.01215   0.00575  -0.0393   0.8801   0.5432
  -3.250  -0.2139   0.01193   0.00570  -0.0382   0.8769   0.5938
  -3.000  -0.1892   0.01180   0.00568  -0.0373   0.8745   0.6378
  -2.750  -0.1647   0.01178   0.00572  -0.0364   0.8715   0.6747
  -2.500  -0.1427   0.01184   0.00580  -0.0351   0.8666   0.7026
  -2.250  -0.1175   0.01185   0.00579  -0.0344   0.8631   0.7249
  -2.000  -0.0910   0.01185   0.00576  -0.0339   0.8604   0.7444
  -1.750  -0.0639   0.01184   0.00572  -0.0335   0.8582   0.7620
  -1.500  -0.0425   0.01194   0.00582  -0.0322   0.8521   0.7762
  -1.250  -0.0164   0.01194   0.00582  -0.0316   0.8484   0.7877
  -1.000   0.0112   0.01190   0.00574  -0.0314   0.8455   0.7976
  -0.750   0.0373   0.01188   0.00570  -0.0309   0.8420   0.8071
  -0.500   0.0611   0.01192   0.00575  -0.0301   0.8362   0.8146
  -0.250   0.0877   0.01186   0.00566  -0.0298   0.8324   0.8232
   0.000   0.1168   0.01178   0.00559  -0.0298   0.8297   0.8293
   0.250   0.1395   0.01182   0.00563  -0.0289   0.8232   0.8374
   0.500   0.1665   0.01177   0.00560  -0.0286   0.8186   0.8432
   0.750   0.1950   0.01166   0.00549  -0.0285   0.8153   0.8499
   1.000   0.2186   0.01167   0.00555  -0.0277   0.8083   0.8562
   1.250   0.2458   0.01159   0.00549  -0.0275   0.8032   0.8623
   1.500   0.2729   0.01148   0.00540  -0.0272   0.7981   0.8688
   1.750   0.2979   0.01144   0.00542  -0.0266   0.7900   0.8745
   2.000   0.3251   0.01131   0.00533  -0.0263   0.7837   0.8812
   2.250   0.3511   0.01123   0.00530  -0.0258   0.7744   0.8869
   2.500   0.3768   0.01113   0.00526  -0.0253   0.7642   0.8936
   2.750   0.4046   0.01099   0.00517  -0.0250   0.7536   0.8998
   3.000   0.4337   0.01084   0.00506  -0.0250   0.7409   0.9056
   3.250   0.4614   0.01070   0.00494  -0.0247   0.7251   0.9128
   3.500   0.4928   0.01058   0.00483  -0.0251   0.7051   0.9178
   3.750   0.5220   0.01052   0.00473  -0.0251   0.6794   0.9244
   4.000   0.5519   0.01056   0.00467  -0.0253   0.6456   0.9301
   4.250   0.5807   0.01072   0.00473  -0.0254   0.6055   0.9362
   4.500   0.6067   0.01100   0.00484  -0.0251   0.5570   0.9434
   4.750   0.6330   0.01146   0.00505  -0.0251   0.4956   0.9499
   5.000   0.6551   0.01209   0.00537  -0.0245   0.4215   0.9585
   5.250   0.6769   0.01295   0.00585  -0.0242   0.3370   0.9675
   5.500   0.7000   0.01387   0.00640  -0.0243   0.2578   0.9769
   5.750   0.7251   0.01474   0.00696  -0.0249   0.1935   0.9865
   6.000   0.7520   0.01556   0.00754  -0.0258   0.1456   0.9957
   6.250   0.7684   0.01615   0.00800  -0.0244   0.1174   1.0000
   6.500   0.7771   0.01659   0.00838  -0.0213   0.1006   1.0000
   6.750   0.7880   0.01707   0.00881  -0.0185   0.0876   1.0000
   7.000   0.8000   0.01760   0.00930  -0.0159   0.0773   1.0000
   7.250   0.8128   0.01810   0.00981  -0.0135   0.0686   1.0000
   7.500   0.8251   0.01865   0.01038  -0.0111   0.0618   1.0000
   7.750   0.8381   0.01924   0.01096  -0.0088   0.0549   1.0000
   8.000   0.8529   0.01979   0.01154  -0.0070   0.0482   1.0000
   8.250   0.8663   0.02048   0.01219  -0.0050   0.0421   1.0000
   8.500   0.8824   0.02105   0.01285  -0.0034   0.0376   1.0000
   8.750   0.8963   0.02180   0.01361  -0.0016   0.0335   1.0000
   9.000   0.9113   0.02252   0.01442   0.0000   0.0295   1.0000
   9.250   0.9257   0.02331   0.01522   0.0015   0.0255   1.0000
   9.500   0.9382   0.02427   0.01627   0.0034   0.0231   1.0000
   9.750   0.9514   0.02521   0.01730   0.0051   0.0209   1.0000
  10.000   0.9632   0.02625   0.01839   0.0068   0.0192   1.0000
  10.250   0.9731   0.02753   0.01975   0.0087   0.0181   1.0000
  10.500   0.9849   0.02874   0.02110   0.0104   0.0171   1.0000
  10.750   0.9963   0.02999   0.02249   0.0120   0.0162   1.0000
  11.000   1.0078   0.03114   0.02374   0.0134   0.0152   1.0000
  11.250   1.0177   0.03243   0.02512   0.0149   0.0145   1.0000
  11.500   1.0249   0.03398   0.02671   0.0164   0.0138   1.0000
  11.750   1.0343   0.03555   0.02848   0.0179   0.0133   1.0000
  12.000   1.0418   0.03734   0.03047   0.0194   0.0129   1.0000
  12.250   1.0481   0.03924   0.03256   0.0209   0.0125   1.0000
  12.500   1.0524   0.04133   0.03485   0.0223   0.0122   1.0000
  12.750   1.0550   0.04354   0.03725   0.0236   0.0118   1.0000
  13.000   1.0555   0.04600   0.03991   0.0249   0.0116   1.0000
  13.250   1.0542   0.04861   0.04275   0.0258   0.0114   1.0000
  13.500   1.0504   0.05162   0.04597   0.0266   0.0113   1.0000
  13.750   1.0448   0.05481   0.04934   0.0270   0.0111   1.0000
  14.000   1.0371   0.05842   0.05317   0.0271   0.0110   1.0000
  14.250   1.0272   0.06248   0.05742   0.0266   0.0109   1.0000
  14.500   1.0143   0.06725   0.06241   0.0254   0.0109   1.0000
  14.750   1.0004   0.07250   0.06786   0.0235   0.0108   1.0000
  15.000   0.9816   0.07906   0.07466   0.0206   0.0108   1.0000
  15.250   0.9586   0.08709   0.08292   0.0162   0.0109   1.0000
  15.500   0.9283   0.09761   0.09371   0.0099   0.0110   1.0000
  15.750   0.8734   0.11612   0.11251  -0.0016   0.0115   1.0000
<< Back to S8064 (s8064-il)

Polar data table (+)

Polar graphs


<< Back to S8064 (s8064-il)