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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 50,000
Max Cl/Cd: 22.63 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9027-il-50000.txt
Download as CSV file: xf-s9027-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9027 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6100   0.09640   0.08923   0.0299   1.0000   0.3511
  -8.000  -0.6238   0.09414   0.08707   0.0293   1.0000   0.3629
  -7.750  -0.7430   0.06178   0.05440  -0.0110   1.0000   0.1476
  -7.500  -0.7378   0.05628   0.04866  -0.0117   1.0000   0.1457
  -7.250  -0.7335   0.05089   0.04281  -0.0123   1.0000   0.1462
  -7.000  -0.7279   0.04583   0.03696  -0.0124   1.0000   0.1488
  -6.750  -0.7078   0.04310   0.03433  -0.0115   1.0000   0.1561
  -6.500  -0.6926   0.03899   0.02954  -0.0109   1.0000   0.1603
  -6.250  -0.6729   0.03636   0.02672  -0.0101   1.0000   0.1709
  -6.000  -0.6526   0.03385   0.02392  -0.0091   1.0000   0.1836
  -5.750  -0.6308   0.03142   0.02120  -0.0082   1.0000   0.1971
  -5.500  -0.6087   0.02957   0.01914  -0.0072   1.0000   0.2167
  -5.250  -0.5853   0.02757   0.01696  -0.0062   1.0000   0.2359
  -5.000  -0.5624   0.02609   0.01537  -0.0051   1.0000   0.2627
  -4.750  -0.5386   0.02452   0.01382  -0.0040   1.0000   0.2908
  -4.500  -0.5159   0.02325   0.01280  -0.0027   1.0000   0.3264
  -4.250  -0.4931   0.02201   0.01171  -0.0013   1.0000   0.3686
  -4.000  -0.4711   0.02091   0.01078   0.0003   1.0000   0.4205
  -3.750  -0.4498   0.01989   0.01006   0.0023   1.0000   0.4793
  -3.500  -0.4298   0.01898   0.00952   0.0049   1.0000   0.5455
  -3.250  -0.4113   0.01819   0.00911   0.0082   1.0000   0.6197
  -3.000  -0.3943   0.01760   0.00888   0.0125   1.0000   0.6984
  -2.750  -0.3765   0.01725   0.00876   0.0172   1.0000   0.7814
  -2.500  -0.3343   0.01740   0.00892   0.0185   1.0000   0.8711
  -2.250  -0.1922   0.01786   0.00865   0.0000   1.0000   0.9627
  -2.000  -0.1124   0.01684   0.00727  -0.0122   1.0000   1.0000
  -1.750  -0.1026   0.01622   0.00658  -0.0112   1.0000   1.0000
  -1.500  -0.0908   0.01578   0.00605  -0.0098   1.0000   1.0000
  -1.250  -0.0775   0.01545   0.00566  -0.0083   1.0000   1.0000
  -1.000  -0.0630   0.01522   0.00537  -0.0068   1.0000   1.0000
  -0.750  -0.0478   0.01506   0.00516  -0.0051   1.0000   1.0000
  -0.500  -0.0320   0.01495   0.00502  -0.0034   1.0000   1.0000
  -0.250  -0.0160   0.01489   0.00493  -0.0017   1.0000   1.0000
   0.000   0.0000   0.01487   0.00490   0.0000   1.0000   1.0000
   0.250   0.0160   0.01489   0.00493   0.0017   1.0000   1.0000
   0.500   0.0320   0.01495   0.00502   0.0034   1.0000   1.0000
   0.750   0.0478   0.01506   0.00516   0.0051   1.0000   1.0000
   1.000   0.0630   0.01522   0.00537   0.0068   1.0000   1.0000
   1.250   0.0775   0.01545   0.00566   0.0083   1.0000   1.0000
   1.500   0.0909   0.01577   0.00605   0.0098   1.0000   1.0000
   1.750   0.1027   0.01622   0.00658   0.0112   1.0000   1.0000
   2.000   0.1126   0.01684   0.00726   0.0122   1.0000   1.0000
   2.250   0.1923   0.01785   0.00864   0.0000   0.9628   1.0000
   2.500   0.3341   0.01740   0.00891  -0.0185   0.8712   1.0000
   2.750   0.3764   0.01725   0.00878  -0.0172   0.7816   1.0000
   3.000   0.3942   0.01760   0.00888  -0.0124   0.6986   1.0000
   3.250   0.4111   0.01819   0.00910  -0.0082   0.6200   1.0000
   3.500   0.4296   0.01898   0.00952  -0.0049   0.5457   1.0000
   3.750   0.4496   0.01988   0.01006  -0.0023   0.4794   1.0000
   4.000   0.4710   0.02091   0.01079  -0.0003   0.4207   1.0000
   4.250   0.4930   0.02201   0.01171   0.0013   0.3688   1.0000
   4.500   0.5157   0.02325   0.01279   0.0027   0.3265   1.0000
   4.750   0.5384   0.02452   0.01382   0.0041   0.2909   1.0000
   5.000   0.5623   0.02608   0.01537   0.0051   0.2628   1.0000
   5.250   0.5852   0.02757   0.01696   0.0062   0.2359   1.0000
   5.500   0.6087   0.02956   0.01913   0.0072   0.2167   1.0000
   5.750   0.6308   0.03142   0.02120   0.0082   0.1972   1.0000
   6.000   0.6526   0.03386   0.02392   0.0091   0.1835   1.0000
   6.250   0.6729   0.03636   0.02671   0.0100   0.1707   1.0000
   6.500   0.6927   0.03901   0.02955   0.0109   0.1603   1.0000
   6.750   0.7079   0.04311   0.03434   0.0115   0.1560   1.0000
   7.000   0.7280   0.04585   0.03700   0.0123   0.1487   1.0000
   7.250   0.7338   0.05092   0.04284   0.0122   0.1462   1.0000
   7.500   0.7382   0.05633   0.04871   0.0116   0.1457   1.0000
   7.750   0.7436   0.06180   0.05442   0.0109   0.1476   1.0000
   8.000   0.6612   0.08493   0.07798  -0.0135   0.2384   1.0000
   8.250   0.7126   0.08019   0.07334   0.0001   0.1782   1.0000
   8.500   0.6069   0.09975   0.09252  -0.0307   0.3405   1.0000
   8.750   0.6115   0.10350   0.09625  -0.0308   0.3296   1.0000
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