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NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 119.22 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s806a-nr-1000000.txt
Download as CSV file: xf-s806a-nr-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S806A Airfoil                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.000  -0.3669   0.04181   0.03845  -0.0487   0.7488   0.0099
  -5.750  -0.3484   0.03838   0.03483  -0.0488   0.7482   0.0099
  -5.500  -0.3277   0.03512   0.03137  -0.0489   0.7475   0.0099
  -5.250  -0.3061   0.03212   0.02815  -0.0488   0.7467   0.0099
  -5.000  -0.2828   0.02936   0.02516  -0.0488   0.7458   0.0099
  -4.750  -0.2583   0.02684   0.02241  -0.0489   0.7447   0.0100
  -4.500  -0.2327   0.02458   0.01992  -0.0489   0.7435   0.0100
  -4.250  -0.2064   0.02255   0.01766  -0.0490   0.7420   0.0100
  -4.000  -0.1790   0.02076   0.01565  -0.0492   0.7404   0.0100
  -3.750  -0.1512   0.01917   0.01385  -0.0493   0.7384   0.0100
  -3.500  -0.1243   0.01407   0.00819  -0.0493   0.7365   0.0120
  -3.250  -0.0958   0.01343   0.00751  -0.0497   0.7344   0.0130
  -3.000  -0.0671   0.01293   0.00696  -0.0501   0.7324   0.0144
  -2.750  -0.0383   0.01253   0.00654  -0.0505   0.7306   0.0168
  -1.500   0.1053   0.00934   0.00326  -0.0515   0.7221   0.0185
  -1.250   0.1350   0.00891   0.00273  -0.0518   0.7198   0.0165
  -1.000   0.1647   0.00868   0.00243  -0.0522   0.7172   0.0155
  -0.750   0.1943   0.00800   0.00212  -0.0528   0.7144   0.1502
  -0.500   0.2196   0.00603   0.00213  -0.0537   0.7115   0.7554
  -0.250   0.2449   0.00605   0.00243  -0.0529   0.7082   0.8407
   0.000   0.2739   0.00624   0.00261  -0.0532   0.7043   0.8508
   0.250   0.3006   0.00640   0.00284  -0.0529   0.6999   0.8750
   0.500   0.3282   0.00645   0.00290  -0.0528   0.6995   0.8886
   0.750   0.3584   0.00644   0.00283  -0.0534   0.6990   0.8904
   1.000   0.3887   0.00637   0.00276  -0.0541   0.6982   0.8897
   1.250   0.4155   0.00641   0.00280  -0.0537   0.6966   0.8996
   1.500   0.4443   0.00628   0.00265  -0.0539   0.6941   0.9035
   1.750   0.4726   0.00618   0.00256  -0.0540   0.6911   0.9074
   2.000   0.5013   0.00610   0.00248  -0.0543   0.6872   0.9106
   2.250   0.5300   0.00603   0.00240  -0.0545   0.6820   0.9137
   2.500   0.5589   0.00599   0.00235  -0.0548   0.6764   0.9168
   2.750   0.5878   0.00598   0.00230  -0.0552   0.6696   0.9193
   3.000   0.6167   0.00598   0.00226  -0.0556   0.6604   0.9224
   3.250   0.6451   0.00601   0.00228  -0.0559   0.6497   0.9258
   3.500   0.6737   0.00591   0.00221  -0.0561   0.6438   0.9292
   3.750   0.7022   0.00589   0.00223  -0.0564   0.6384   0.9329
   4.000   0.7279   0.00616   0.00211  -0.0561   0.5581   0.9370
   4.250   0.7439   0.00866   0.00314  -0.0557   0.2450   0.9399
   4.500   0.7667   0.00945   0.00354  -0.0555   0.1632   0.9450
   4.750   0.7919   0.00977   0.00374  -0.0554   0.1345   0.9502
   5.000   0.8157   0.01028   0.00405  -0.0551   0.1036   0.9567
   5.250   0.8427   0.01045   0.00422  -0.0553   0.0990   0.9643
   5.500   0.8699   0.01078   0.00448  -0.0557   0.0826   0.9762
   5.750   0.8996   0.01104   0.00471  -0.0566   0.0729   1.0000
   6.000   0.9263   0.01138   0.00499  -0.0569   0.0626   1.0000
   6.250   0.9526   0.01172   0.00528  -0.0571   0.0532   1.0000
   6.500   0.9784   0.01208   0.00559  -0.0573   0.0468   1.0000
   6.750   1.0038   0.01245   0.00591  -0.0573   0.0408   1.0000
   7.000   1.0292   0.01278   0.00623  -0.0573   0.0366   1.0000
   7.250   1.0539   0.01316   0.00658  -0.0572   0.0325   1.0000
   7.500   1.0725   0.01356   0.00709  -0.0557   0.0255   1.0000
   7.750   1.0938   0.01406   0.00752  -0.0550   0.0178   1.0000
   8.000   1.1148   0.01457   0.00799  -0.0542   0.0123   1.0000
   8.250   1.1364   0.01500   0.00841  -0.0535   0.0093   1.0000
   8.500   1.1579   0.01542   0.00884  -0.0529   0.0084   1.0000
   8.750   1.1785   0.01587   0.00929  -0.0521   0.0075   1.0000
   9.000   1.1984   0.01634   0.00975  -0.0512   0.0068   1.0000
   9.250   1.2169   0.01684   0.01023  -0.0501   0.0059   1.0000
   9.500   1.2347   0.01736   0.01076  -0.0488   0.0051   1.0000
   9.750   1.2533   0.01786   0.01133  -0.0479   0.0054   1.0000
  10.000   1.2672   0.01852   0.01202  -0.0461   0.0046   1.0000
  10.250   1.2806   0.01928   0.01284  -0.0445   0.0041   1.0000
  10.500   1.2918   0.02027   0.01393  -0.0426   0.0037   1.0000
  10.750   1.3035   0.02130   0.01506  -0.0409   0.0035   1.0000
  11.000   1.3140   0.02245   0.01632  -0.0392   0.0033   1.0000
  11.250   1.3214   0.02383   0.01782  -0.0372   0.0032   1.0000
  11.500   1.3290   0.02522   0.01933  -0.0352   0.0032   1.0000
  11.750   1.3360   0.02671   0.02094  -0.0334   0.0032   1.0000
  12.000   1.3399   0.02848   0.02284  -0.0314   0.0031   1.0000
  12.250   1.3464   0.03009   0.02456  -0.0297   0.0031   1.0000
  12.500   1.3440   0.03236   0.02702  -0.0269   0.0031   1.0000
  12.750   1.3400   0.03485   0.02969  -0.0243   0.0030   1.0000
  13.000   1.3356   0.03757   0.03260  -0.0220   0.0030   1.0000
  13.250   1.3294   0.04059   0.03582  -0.0197   0.0029   1.0000
  13.500   1.3229   0.04374   0.03917  -0.0176   0.0029   1.0000
  13.750   1.3115   0.04734   0.04298  -0.0158   0.0029   1.0000
  14.000   1.3005   0.05109   0.04694  -0.0143   0.0028   1.0000
  14.250   1.2883   0.05518   0.05122  -0.0130   0.0028   1.0000
  14.500   1.2747   0.05967   0.05589  -0.0127   0.0028   1.0000
  14.750   1.2627   0.06419   0.06059  -0.0125   0.0028   1.0000
  15.000   1.2470   0.06952   0.06608  -0.0132   0.0028   1.0000
  15.250   1.2332   0.07470   0.07143  -0.0140   0.0029   1.0000
  15.500   1.2180   0.08062   0.07749  -0.0158   0.0029   1.0000
  15.750   1.2036   0.08690   0.08391  -0.0181   0.0029   1.0000
  16.000   1.1894   0.09349   0.09064  -0.0210   0.0029   1.0000
  16.250   1.1731   0.10096   0.09825  -0.0247   0.0029   1.0000
  16.500   1.1557   0.10915   0.10657  -0.0290   0.0029   1.0000
  16.750   1.1375   0.11797   0.11552  -0.0340   0.0030   1.0000
  17.000   1.1190   0.12718   0.12486  -0.0392   0.0030   1.0000
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