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S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S8065 (11% version of S8064) (s8065-il)
Reynolds number: 200,000
Max Cl/Cd: 69 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8065-il-200000.txt
Download as CSV file: xf-s8065-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4031   0.11319   0.10986  -0.0319   1.0000   0.0529
 -11.500  -0.4175   0.10781   0.10453  -0.0367   1.0000   0.0537
 -11.250  -0.4240   0.10271   0.09945  -0.0399   1.0000   0.0539
 -11.000  -0.4300   0.09602   0.09280  -0.0413   1.0000   0.0547
 -10.750  -0.4190   0.09306   0.08983  -0.0399   1.0000   0.0557
 -10.500  -0.4146   0.08957   0.08635  -0.0401   1.0000   0.0568
 -10.250  -0.4146   0.08542   0.08223  -0.0411   1.0000   0.0579
 -10.000  -0.4190   0.08064   0.07747  -0.0427   1.0000   0.0590
  -9.750  -0.4271   0.07527   0.07213  -0.0450   1.0000   0.0598
  -9.500  -0.4405   0.06910   0.06600  -0.0481   1.0000   0.0606
  -9.250  -0.4672   0.06130   0.05824  -0.0535   1.0000   0.0610
  -9.000  -0.4999   0.05685   0.05378  -0.0541   1.0000   0.0604
  -8.750  -0.5365   0.05467   0.05161  -0.0505   1.0000   0.0600
  -8.500  -0.5730   0.05341   0.05034  -0.0450   1.0000   0.0596
  -8.250  -0.6029   0.05156   0.04845  -0.0400   1.0000   0.0595
  -8.000  -0.6245   0.04909   0.04591  -0.0362   1.0000   0.0599
  -7.750  -0.6418   0.04630   0.04303  -0.0326   1.0000   0.0606
  -7.500  -0.6554   0.04332   0.03986  -0.0293   1.0000   0.0618
  -7.250  -0.7300   0.03947   0.03433  -0.0206   1.0000   0.0295
  -7.000  -0.7210   0.03314   0.02722  -0.0187   0.9977   0.0258
  -6.750  -0.6973   0.02905   0.02230  -0.0180   0.9949   0.0241
  -6.500  -0.6714   0.02657   0.01943  -0.0181   0.9923   0.0241
  -6.250  -0.6452   0.02426   0.01686  -0.0182   0.9896   0.0249
  -6.000  -0.6159   0.02267   0.01512  -0.0188   0.9869   0.0259
  -5.750  -0.5838   0.02167   0.01400  -0.0200   0.9844   0.0286
  -5.500  -0.5540   0.02095   0.01310  -0.0205   0.9814   0.0317
  -5.250  -0.5309   0.01912   0.01130  -0.0200   0.9778   0.0359
  -5.000  -0.5030   0.01796   0.01009  -0.0203   0.9743   0.0456
  -4.750  -0.4713   0.01704   0.00926  -0.0215   0.9715   0.0714
  -4.500  -0.4473   0.01640   0.00874  -0.0213   0.9670   0.1031
  -4.250  -0.4218   0.01561   0.00826  -0.0215   0.9626   0.1567
  -4.000  -0.3942   0.01455   0.00783  -0.0225   0.9591   0.2810
  -3.750  -0.3735   0.01364   0.00766  -0.0218   0.9546   0.4497
  -3.500  -0.3525   0.01318   0.00764  -0.0206   0.9491   0.5646
  -3.250  -0.3230   0.01300   0.00778  -0.0206   0.9455   0.6538
  -3.000  -0.2941   0.01308   0.00795  -0.0205   0.9414   0.7116
  -2.750  -0.2711   0.01317   0.00804  -0.0192   0.9354   0.7476
  -2.500  -0.2383   0.01329   0.00814  -0.0199   0.9317   0.7801
  -2.250  -0.2008   0.01344   0.00827  -0.0214   0.9294   0.8061
  -2.000  -0.1858   0.01354   0.00834  -0.0185   0.9213   0.8277
  -1.750  -0.1519   0.01366   0.00844  -0.0192   0.9179   0.8482
  -1.500  -0.1135   0.01379   0.00854  -0.0208   0.9157   0.8678
  -1.250  -0.0986   0.01391   0.00867  -0.0177   0.9073   0.8863
  -1.000  -0.0604   0.01406   0.00877  -0.0192   0.9044   0.9026
  -0.750  -0.0167   0.01418   0.00885  -0.0219   0.9026   0.9154
  -0.500   0.0133   0.01432   0.00897  -0.0222   0.8965   0.9277
  -0.250   0.0607   0.01443   0.00904  -0.0260   0.8934   0.9337
   0.000   0.1032   0.01444   0.00902  -0.0288   0.8904   0.9418
   0.250   0.1572   0.01443   0.00898  -0.0340   0.8889   0.9445
   0.500   0.2102   0.01435   0.00890  -0.0389   0.8872   0.9472
   0.750   0.2421   0.01441   0.00897  -0.0399   0.8790   0.9555
   1.000   0.2915   0.01422   0.00881  -0.0441   0.8757   0.9582
   1.250   0.3398   0.01396   0.00856  -0.0479   0.8728   0.9610
   1.500   0.3741   0.01387   0.00851  -0.0493   0.8634   0.9678
   1.750   0.4159   0.01347   0.00816  -0.0516   0.8588   0.9719
   2.000   0.4544   0.01321   0.00795  -0.0536   0.8483   0.9770
   2.250   0.4883   0.01286   0.00764  -0.0544   0.8383   0.9834
   2.500   0.5288   0.01227   0.00711  -0.0563   0.8288   0.9874
   2.750   0.5651   0.01175   0.00664  -0.0575   0.8156   0.9930
   3.000   0.6018   0.01126   0.00622  -0.0591   0.7975   0.9986
   3.250   0.6247   0.01093   0.00595  -0.0579   0.7794   1.0000
   3.500   0.6430   0.01062   0.00567  -0.0558   0.7604   1.0000
   3.750   0.6606   0.01041   0.00547  -0.0536   0.7362   1.0000
   4.000   0.6787   0.01024   0.00527  -0.0514   0.7078   1.0000
   4.250   0.6959   0.01020   0.00515  -0.0491   0.6708   1.0000
   4.500   0.7114   0.01031   0.00511  -0.0465   0.6236   1.0000
   4.750   0.7240   0.01060   0.00516  -0.0435   0.5621   1.0000
   5.000   0.7320   0.01114   0.00532  -0.0397   0.4797   1.0000
   5.250   0.7356   0.01198   0.00566  -0.0355   0.3814   1.0000
   5.500   0.7377   0.01307   0.00617  -0.0312   0.2776   1.0000
   5.750   0.7418   0.01425   0.00682  -0.0274   0.1878   1.0000
   6.000   0.7501   0.01532   0.00752  -0.0243   0.1355   1.0000
   6.250   0.7623   0.01621   0.00825  -0.0217   0.1102   1.0000
   6.500   0.7759   0.01708   0.00904  -0.0194   0.0951   1.0000
   6.750   0.7914   0.01789   0.00983  -0.0174   0.0836   1.0000
   7.000   0.8072   0.01876   0.01070  -0.0155   0.0741   1.0000
   7.250   0.8233   0.01967   0.01157  -0.0138   0.0647   1.0000
   7.500   0.8415   0.02037   0.01233  -0.0123   0.0571   1.0000
   7.750   0.8588   0.02160   0.01360  -0.0107   0.0500   1.0000
   8.000   0.8762   0.02295   0.01489  -0.0094   0.0428   1.0000
   8.250   0.8967   0.02408   0.01619  -0.0081   0.0380   1.0000
   8.500   0.9168   0.02535   0.01750  -0.0071   0.0345   1.0000
   8.750   0.9428   0.02851   0.02080  -0.0072   0.0317   1.0000
   9.000   0.9608   0.02957   0.02214  -0.0056   0.0296   1.0000
   9.250   0.9789   0.03121   0.02402  -0.0043   0.0277   1.0000
   9.500   0.9957   0.03335   0.02640  -0.0028   0.0267   1.0000
   9.750   1.0091   0.03563   0.02894  -0.0011   0.0259   1.0000
  10.000   1.0189   0.03835   0.03197   0.0010   0.0255   1.0000
  10.250   1.0236   0.04148   0.03544   0.0036   0.0253   1.0000
  10.500   1.0221   0.04482   0.03915   0.0068   0.0253   1.0000
  10.750   0.9961   0.04989   0.04482   0.0126   0.0266   1.0000
  11.000   0.9716   0.05424   0.04954   0.0171   0.0274   1.0000
  11.250   0.9478   0.05857   0.05414   0.0201   0.0281   1.0000
  11.500   0.9249   0.06292   0.05872   0.0218   0.0288   1.0000
  11.750   0.9006   0.06767   0.06366   0.0223   0.0292   1.0000
  12.000   0.8773   0.07284   0.06898   0.0214   0.0296   1.0000
  12.250   0.8524   0.07894   0.07522   0.0189   0.0300   1.0000
  12.500   0.8271   0.08615   0.08255   0.0146   0.0303   1.0000
  12.750   0.8029   0.09470   0.09119   0.0090   0.0309   1.0000
  13.000   0.6767   0.10063   0.09743   0.0049   0.0309   1.0000
  13.250   0.6571   0.10876   0.10554   0.0011   0.0318   1.0000
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