Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S8065 (11% version of S8064) (s8065-il)
Reynolds number: 500,000
Max Cl/Cd: 64.26 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8065-il-500000-n5.txt
Download as CSV file: xf-s8065-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8065 (11% version of S8064)                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7019   0.06300   0.06057  -0.0491   1.0000   0.0048
 -11.750  -0.7292   0.05355   0.05094  -0.0568   1.0000   0.0047
 -11.500  -0.7449   0.04829   0.04552  -0.0602   1.0000   0.0047
 -11.250  -0.7770   0.04225   0.03922  -0.0617   1.0000   0.0045
 -11.000  -0.7908   0.03898   0.03576  -0.0610   1.0000   0.0045
 -10.500  -0.7867   0.03295   0.02909  -0.0616   0.9561   0.0048
 -10.250  -0.7898   0.03028   0.02608  -0.0588   0.9443   0.0047
 -10.000  -0.7847   0.02828   0.02377  -0.0566   0.9369   0.0048
  -9.750  -0.7746   0.02671   0.02192  -0.0547   0.9316   0.0049
  -9.500  -0.7631   0.02501   0.01996  -0.0529   0.9270   0.0049
  -9.250  -0.7494   0.02341   0.01811  -0.0513   0.9225   0.0050
  -9.000  -0.7334   0.02207   0.01655  -0.0499   0.9189   0.0050
  -8.750  -0.7162   0.02086   0.01514  -0.0486   0.9158   0.0050
  -8.500  -0.6972   0.01973   0.01384  -0.0476   0.9125   0.0051
  -8.250  -0.6774   0.01872   0.01268  -0.0466   0.9092   0.0051
  -8.000  -0.6572   0.01782   0.01164  -0.0456   0.9060   0.0052
  -7.750  -0.6371   0.01692   0.01060  -0.0445   0.9032   0.0053
  -7.500  -0.6175   0.01595   0.00950  -0.0434   0.9006   0.0054
  -7.250  -0.5959   0.01516   0.00864  -0.0426   0.8977   0.0056
  -7.000  -0.5732   0.01454   0.00793  -0.0419   0.8949   0.0059
  -6.750  -0.5499   0.01401   0.00733  -0.0413   0.8921   0.0062
  -6.500  -0.5263   0.01352   0.00675  -0.0407   0.8896   0.0067
  -6.250  -0.5023   0.01310   0.00624  -0.0401   0.8873   0.0070
  -6.000  -0.4774   0.01271   0.00578  -0.0397   0.8847   0.0076
  -5.750  -0.4527   0.01229   0.00531  -0.0393   0.8818   0.0085
  -5.500  -0.4278   0.01193   0.00492  -0.0389   0.8790   0.0104
  -5.250  -0.4032   0.01153   0.00452  -0.0384   0.8764   0.0163
  -5.000  -0.3785   0.01116   0.00418  -0.0380   0.8740   0.0283
  -4.750  -0.3532   0.01085   0.00391  -0.0377   0.8716   0.0406
  -4.500  -0.3277   0.01053   0.00366  -0.0374   0.8686   0.0577
  -4.250  -0.3020   0.01025   0.00343  -0.0372   0.8656   0.0756
  -4.000  -0.2773   0.00985   0.00319  -0.0368   0.8626   0.1130
  -3.750  -0.2526   0.00947   0.00296  -0.0365   0.8600   0.1544
  -3.500  -0.2274   0.00914   0.00276  -0.0362   0.8573   0.1962
  -3.250  -0.2028   0.00872   0.00257  -0.0358   0.8537   0.2573
  -3.000  -0.1786   0.00828   0.00238  -0.0354   0.8502   0.3290
  -2.750  -0.1544   0.00788   0.00222  -0.0349   0.8470   0.4008
  -2.500  -0.1295   0.00757   0.00208  -0.0345   0.8441   0.4617
  -2.250  -0.1042   0.00730   0.00199  -0.0341   0.8403   0.5155
  -2.000  -0.0785   0.00708   0.00192  -0.0338   0.8362   0.5600
  -1.750  -0.0528   0.00688   0.00184  -0.0334   0.8326   0.6018
  -1.500  -0.0270   0.00672   0.00178  -0.0329   0.8294   0.6423
  -1.250  -0.0008   0.00660   0.00180  -0.0326   0.8247   0.6791
  -1.000   0.0259   0.00653   0.00179  -0.0323   0.8201   0.7085
  -0.750   0.0529   0.00647   0.00177  -0.0320   0.8161   0.7317
  -0.500   0.0801   0.00644   0.00177  -0.0318   0.8110   0.7499
  -0.250   0.1074   0.00640   0.00176  -0.0317   0.8053   0.7644
   0.000   0.1348   0.00637   0.00173  -0.0315   0.8003   0.7759
   0.250   0.1623   0.00634   0.00174  -0.0314   0.7928   0.7854
   0.500   0.1899   0.00631   0.00170  -0.0313   0.7856   0.7943
   0.750   0.2172   0.00628   0.00170  -0.0312   0.7758   0.8023
   1.000   0.2446   0.00627   0.00168  -0.0310   0.7646   0.8104
   1.250   0.2717   0.00625   0.00166  -0.0308   0.7513   0.8175
   1.500   0.2987   0.00626   0.00164  -0.0305   0.7354   0.8251
   1.750   0.3251   0.00629   0.00163  -0.0302   0.7169   0.8318
   2.000   0.3514   0.00636   0.00165  -0.0298   0.6948   0.8392
   2.250   0.3770   0.00646   0.00169  -0.0293   0.6696   0.8460
   2.500   0.4022   0.00661   0.00175  -0.0287   0.6394   0.8536
   2.750   0.4262   0.00681   0.00184  -0.0280   0.6017   0.8609
   3.250   0.4723   0.00735   0.00209  -0.0262   0.5116   0.8777
   3.500   0.4942   0.00770   0.00227  -0.0252   0.4579   0.8871
   3.750   0.5151   0.00814   0.00250  -0.0240   0.3958   0.8980
   4.000   0.5358   0.00864   0.00276  -0.0229   0.3300   0.9100
   4.250   0.5569   0.00921   0.00306  -0.0219   0.2590   0.9238
   4.500   0.5817   0.00976   0.00338  -0.0217   0.2009   0.9382
   4.750   0.6115   0.01025   0.00372  -0.0226   0.1573   0.9515
   5.000   0.6435   0.01072   0.00405  -0.0240   0.1224   0.9634
   5.250   0.6752   0.01118   0.00440  -0.0253   0.0945   0.9745
   5.500   0.7058   0.01160   0.00475  -0.0264   0.0760   0.9845
   5.750   0.7377   0.01201   0.00510  -0.0277   0.0618   0.9916
   6.000   0.7691   0.01243   0.00547  -0.0290   0.0493   0.9984
   6.250   0.7918   0.01276   0.00578  -0.0283   0.0424   1.0000
   6.500   0.8107   0.01309   0.00610  -0.0268   0.0365   1.0000
   6.750   0.8302   0.01343   0.00644  -0.0254   0.0321   1.0000
   7.000   0.8498   0.01379   0.00681  -0.0241   0.0286   1.0000
   7.250   0.8700   0.01413   0.00718  -0.0228   0.0250   1.0000
   7.500   0.8895   0.01456   0.00759  -0.0215   0.0212   1.0000
   7.750   0.9095   0.01496   0.00802  -0.0203   0.0178   1.0000
   8.000   0.9286   0.01545   0.00853  -0.0190   0.0145   1.0000
   8.250   0.9475   0.01594   0.00904  -0.0177   0.0123   1.0000
   8.500   0.9657   0.01651   0.00963  -0.0162   0.0108   1.0000
   8.750   0.9842   0.01703   0.01022  -0.0148   0.0099   1.0000
   9.000   1.0020   0.01760   0.01084  -0.0134   0.0093   1.0000
   9.250   1.0181   0.01821   0.01151  -0.0117   0.0087   1.0000
   9.500   1.0322   0.01891   0.01228  -0.0096   0.0083   1.0000
   9.750   1.0446   0.01973   0.01317  -0.0074   0.0079   1.0000
  10.000   1.0587   0.02044   0.01398  -0.0054   0.0077   1.0000
  10.250   1.0718   0.02125   0.01488  -0.0035   0.0075   1.0000
  10.500   1.0848   0.02208   0.01581  -0.0016   0.0074   1.0000
  10.750   1.0967   0.02302   0.01686   0.0004   0.0071   1.0000
  11.000   1.1082   0.02400   0.01795   0.0023   0.0069   1.0000
  11.250   1.1196   0.02499   0.01904   0.0040   0.0066   1.0000
  11.500   1.1309   0.02599   0.02014   0.0057   0.0064   1.0000
  11.750   1.1400   0.02719   0.02147   0.0076   0.0063   1.0000
  12.000   1.1500   0.02829   0.02265   0.0092   0.0060   1.0000
  12.250   1.1567   0.02969   0.02417   0.0110   0.0058   1.0000
  12.500   1.1613   0.03128   0.02588   0.0128   0.0057   1.0000
  12.750   1.1636   0.03312   0.02785   0.0146   0.0056   1.0000
  13.000   1.1651   0.03508   0.02996   0.0163   0.0055   1.0000
  13.250   1.1590   0.03787   0.03293   0.0181   0.0054   1.0000
  13.500   1.1573   0.04031   0.03554   0.0194   0.0053   1.0000
  13.750   1.1573   0.04265   0.03804   0.0202   0.0053   1.0000
  14.000   1.1557   0.04526   0.04082   0.0208   0.0052   1.0000
  14.250   1.1451   0.04908   0.04483   0.0211   0.0052   1.0000
  14.500   1.1402   0.05242   0.04834   0.0207   0.0052   1.0000
  14.750   1.1313   0.05653   0.05263   0.0199   0.0051   1.0000
  15.000   1.1219   0.06104   0.05731   0.0184   0.0051   1.0000
  15.250   1.1101   0.06632   0.06277   0.0161   0.0050   1.0000
  15.500   1.0931   0.07293   0.06957   0.0128   0.0050   1.0000
  15.750   1.0729   0.08067   0.07748   0.0085   0.0051   1.0000
  16.000   1.0551   0.08871   0.08569   0.0037   0.0051   1.0000
  16.250   1.0313   0.09862   0.09577  -0.0023   0.0051   1.0000
  16.500   1.0006   0.11055   0.10787  -0.0092   0.0052   1.0000
  16.750   0.9785   0.12098   0.11842  -0.0151   0.0052   1.0000
  17.000   0.9448   0.13441   0.13197  -0.0224   0.0053   1.0000
  17.250   0.9117   0.14863   0.14631  -0.0299   0.0055   1.0000
<< Back to S8065 (11% version of S8064) (s8065-il)

Polar data table (+)

Polar graphs


<< Back to S8065 (11% version of S8064) (s8065-il)