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S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8065 (11% version of S8064) (s8065-il)
Reynolds number: 50,000
Max Cl/Cd: 31.2 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8065-il-50000-n5.txt
Download as CSV file: xf-s8065-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5253   0.09649   0.08943  -0.0405   1.0000   0.0369
 -10.500  -0.5305   0.09057   0.08357  -0.0437   1.0000   0.0366
 -10.250  -0.5391   0.08436   0.07739  -0.0476   1.0000   0.0362
 -10.000  -0.5526   0.07834   0.07139  -0.0515   1.0000   0.0358
  -9.750  -0.5691   0.07321   0.06625  -0.0543   1.0000   0.0354
  -9.500  -0.5873   0.06905   0.06206  -0.0552   1.0000   0.0350
  -9.250  -0.6081   0.06572   0.05868  -0.0540   1.0000   0.0348
  -9.000  -0.6264   0.06274   0.05562  -0.0516   1.0000   0.0346
  -8.750  -0.6424   0.05990   0.05265  -0.0487   1.0000   0.0345
  -8.500  -0.6570   0.05710   0.04965  -0.0453   1.0000   0.0346
  -8.250  -0.6685   0.05432   0.04664  -0.0417   1.0000   0.0349
  -8.000  -0.6766   0.05155   0.04356  -0.0381   1.0000   0.0354
  -7.750  -0.6810   0.04874   0.04038  -0.0347   1.0000   0.0361
  -7.500  -0.6814   0.04596   0.03715  -0.0314   1.0000   0.0369
  -7.250  -0.6779   0.04327   0.03398  -0.0283   1.0000   0.0381
  -7.000  -0.6700   0.04097   0.03155  -0.0261   1.0000   0.0398
  -6.750  -0.6591   0.03886   0.02919  -0.0239   1.0000   0.0416
  -6.500  -0.6455   0.03662   0.02663  -0.0218   1.0000   0.0436
  -6.250  -0.6293   0.03458   0.02415  -0.0198   1.0000   0.0470
  -6.000  -0.6133   0.03281   0.02224  -0.0180   1.0000   0.0521
  -5.750  -0.5957   0.03131   0.02050  -0.0162   1.0000   0.0592
  -5.500  -0.5788   0.02989   0.01905  -0.0145   1.0000   0.0684
  -5.250  -0.5616   0.02856   0.01764  -0.0127   1.0000   0.0818
  -5.000  -0.5444   0.02732   0.01629  -0.0109   1.0000   0.0996
  -4.750  -0.5282   0.02609   0.01513  -0.0091   1.0000   0.1215
  -4.500  -0.5119   0.02493   0.01402  -0.0075   1.0000   0.1538
  -4.250  -0.4959   0.02367   0.01304  -0.0061   1.0000   0.2035
  -4.000  -0.4820   0.02228   0.01222  -0.0045   1.0000   0.2940
  -3.750  -0.4715   0.02109   0.01185  -0.0017   1.0000   0.4393
  -3.500  -0.4596   0.02057   0.01191   0.0021   1.0000   0.5768
  -3.250  -0.4460   0.02057   0.01217   0.0062   1.0000   0.6732
  -3.000  -0.4318   0.02071   0.01224   0.0098   1.0000   0.7428
  -2.750  -0.4112   0.02095   0.01237   0.0122   0.9980   0.7990
  -2.500  -0.3780   0.02140   0.01264   0.0125   0.9938   0.8495
  -2.250  -0.3335   0.02191   0.01288   0.0104   0.9908   0.8932
  -2.000  -0.2766   0.02244   0.01308   0.0053   0.9891   0.9276
  -1.750  -0.2120   0.02281   0.01312  -0.0021   0.9878   0.9482
  -1.500  -0.1539   0.02303   0.01304  -0.0088   0.9854   0.9649
  -1.250  -0.0996   0.02317   0.01294  -0.0150   0.9823   0.9801
  -1.000  -0.0482   0.02324   0.01281  -0.0208   0.9786   0.9945
  -0.750  -0.0090   0.02332   0.01275  -0.0246   0.9729   1.0000
  -0.500   0.0171   0.02336   0.01268  -0.0257   0.9644   1.0000
  -0.250   0.0492   0.02352   0.01274  -0.0278   0.9574   1.0000
   0.000   0.0720   0.02360   0.01276  -0.0281   0.9479   1.0000
   0.250   0.0987   0.02376   0.01286  -0.0290   0.9396   1.0000
   0.500   0.1275   0.02395   0.01302  -0.0302   0.9315   1.0000
   0.750   0.1496   0.02412   0.01316  -0.0301   0.9218   1.0000
   1.000   0.1814   0.02437   0.01339  -0.0316   0.9143   1.0000
   1.250   0.2043   0.02458   0.01360  -0.0315   0.9043   1.0000
   1.500   0.2276   0.02481   0.01385  -0.0314   0.8944   1.0000
   1.750   0.2637   0.02507   0.01415  -0.0335   0.8872   1.0000
   2.000   0.2831   0.02530   0.01440  -0.0325   0.8757   1.0000
   2.250   0.3060   0.02554   0.01469  -0.0320   0.8647   1.0000
   2.500   0.3362   0.02575   0.01501  -0.0328   0.8551   1.0000
   2.750   0.3680   0.02593   0.01528  -0.0337   0.8451   1.0000
   3.000   0.3906   0.02610   0.01555  -0.0329   0.8324   1.0000
   3.250   0.4155   0.02623   0.01582  -0.0324   0.8194   1.0000
   3.500   0.4417   0.02630   0.01603  -0.0320   0.8060   1.0000
   3.750   0.4687   0.02627   0.01615  -0.0316   0.7918   1.0000
   4.000   0.4969   0.02611   0.01620  -0.0311   0.7765   1.0000
   4.250   0.5283   0.02572   0.01602  -0.0307   0.7602   1.0000
   4.500   0.5534   0.02532   0.01582  -0.0292   0.7399   1.0000
   4.750   0.5857   0.02450   0.01523  -0.0281   0.7177   1.0000
   5.000   0.6132   0.02372   0.01468  -0.0262   0.6887   1.0000
   5.250   0.6361   0.02311   0.01423  -0.0236   0.6507   1.0000
   5.500   0.6633   0.02247   0.01366  -0.0214   0.5997   1.0000
   5.750   0.6868   0.02219   0.01326  -0.0189   0.5245   1.0000
   6.000   0.7041   0.02257   0.01319  -0.0158   0.4194   1.0000
   6.250   0.7104   0.02374   0.01371  -0.0121   0.3191   1.0000
   6.500   0.7150   0.02524   0.01465  -0.0088   0.2437   1.0000
   6.750   0.7230   0.02676   0.01581  -0.0062   0.1938   1.0000
   7.000   0.7339   0.02823   0.01703  -0.0042   0.1598   1.0000
   7.250   0.7486   0.02965   0.01836  -0.0024   0.1378   1.0000
   7.500   0.7656   0.03103   0.01975  -0.0011   0.1191   1.0000
   7.750   0.7878   0.03250   0.02127  -0.0003   0.1051   1.0000
   8.000   0.8131   0.03406   0.02293   0.0001   0.0924   1.0000
   8.250   0.8410   0.03589   0.02489   0.0002   0.0819   1.0000
   8.500   0.8656   0.03783   0.02686   0.0005   0.0731   1.0000
   8.750   0.8880   0.03989   0.02928   0.0012   0.0652   1.0000
   9.000   0.9075   0.04226   0.03186   0.0020   0.0592   1.0000
   9.250   0.9237   0.04477   0.03475   0.0033   0.0541   1.0000
   9.500   0.9377   0.04708   0.03711   0.0044   0.0504   1.0000
   9.750   0.9441   0.05013   0.04066   0.0065   0.0477   1.0000
  10.000   0.9458   0.05331   0.04431   0.0089   0.0455   1.0000
  10.250   0.9438   0.05667   0.04806   0.0114   0.0443   1.0000
  10.500   0.9364   0.05989   0.05159   0.0141   0.0437   1.0000
  10.750   0.9244   0.06328   0.05525   0.0166   0.0432   1.0000
  11.000   0.9093   0.06694   0.05917   0.0185   0.0430   1.0000
  11.250   0.8912   0.07099   0.06345   0.0196   0.0428   1.0000
  11.500   0.8695   0.07571   0.06838   0.0196   0.0430   1.0000
  11.750   0.8446   0.08137   0.07422   0.0180   0.0435   1.0000
  12.000   0.8181   0.08819   0.08116   0.0147   0.0441   1.0000
  12.250   0.7917   0.09645   0.08950   0.0097   0.0449   1.0000
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