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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 200,000
Max Cl/Cd: 48.9 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8025-il-200000-n5.txt
Download as CSV file: xf-s8025-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8025 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.8193   0.05257   0.04886  -0.0114   1.0000   0.0071
  -9.250  -0.8396   0.04638   0.04228  -0.0130   1.0000   0.0070
  -9.000  -0.8446   0.04148   0.03696  -0.0133   1.0000   0.0070
  -8.750  -0.8413   0.03725   0.03226  -0.0130   1.0000   0.0070
  -8.500  -0.8316   0.03379   0.02837  -0.0124   1.0000   0.0071
  -8.250  -0.8173   0.03095   0.02513  -0.0117   1.0000   0.0072
  -8.000  -0.8003   0.02849   0.02232  -0.0110   1.0000   0.0074
  -7.750  -0.7812   0.02636   0.01985  -0.0102   1.0000   0.0076
  -7.500  -0.7607   0.02449   0.01769  -0.0095   1.0000   0.0079
  -7.250  -0.7391   0.02280   0.01576  -0.0087   1.0000   0.0083
  -7.000  -0.7168   0.02135   0.01410  -0.0080   1.0000   0.0087
  -6.750  -0.6935   0.02019   0.01275  -0.0073   1.0000   0.0095
  -6.500  -0.6707   0.01905   0.01154  -0.0068   1.0000   0.0106
  -6.250  -0.6467   0.01812   0.01051  -0.0062   1.0000   0.0119
  -6.000  -0.6226   0.01713   0.00934  -0.0056   1.0000   0.0129
  -5.750  -0.5986   0.01608   0.00816  -0.0049   1.0000   0.0143
  -5.500  -0.5740   0.01524   0.00722  -0.0043   1.0000   0.0170
  -5.250  -0.5492   0.01438   0.00634  -0.0037   1.0000   0.0244
  -5.000  -0.5245   0.01360   0.00567  -0.0032   1.0000   0.0455
  -4.750  -0.4993   0.01300   0.00517  -0.0028   1.0000   0.0718
  -4.500  -0.4739   0.01249   0.00477  -0.0024   1.0000   0.0987
  -4.250  -0.4484   0.01202   0.00440  -0.0021   1.0000   0.1254
  -4.000  -0.4228   0.01159   0.00405  -0.0017   1.0000   0.1533
  -3.750  -0.3971   0.01120   0.00374  -0.0012   1.0000   0.1803
  -3.500  -0.3715   0.01084   0.00344  -0.0008   1.0000   0.2110
  -3.250  -0.3459   0.01047   0.00320  -0.0004   1.0000   0.2459
  -2.750  -0.2951   0.00981   0.00279   0.0006   1.0000   0.3241
  -2.500  -0.2703   0.00945   0.00263   0.0012   1.0000   0.3754
  -2.250  -0.2457   0.00913   0.00250   0.0018   1.0000   0.4265
  -2.000  -0.2211   0.00885   0.00241   0.0025   1.0000   0.4749
  -1.750  -0.1916   0.00858   0.00233   0.0022   0.9899   0.5280
  -1.500  -0.1533   0.00834   0.00229   0.0001   0.9522   0.5866
  -1.250  -0.1141   0.00816   0.00226  -0.0019   0.9036   0.6417
  -1.000  -0.0815   0.00805   0.00220  -0.0022   0.8481   0.6912
  -0.750  -0.0559   0.00802   0.00216  -0.0010   0.7949   0.7349
  -0.500  -0.0322   0.00804   0.00213   0.0006   0.7470   0.7762
  -0.250  -0.0082   0.00808   0.00211   0.0021   0.7035   0.8202
   0.000   0.0185   0.00814   0.00210   0.0031   0.6635   0.8669
   0.250   0.0514   0.00825   0.00209   0.0026   0.6241   0.9111
   0.500   0.0898   0.00838   0.00206   0.0007   0.5851   0.9461
   0.750   0.1287   0.00852   0.00204  -0.0014   0.5483   0.9745
   1.000   0.1675   0.00868   0.00202  -0.0037   0.5126   0.9972
   1.250   0.1942   0.00885   0.00203  -0.0035   0.4823   1.0000
   1.750   0.2437   0.00923   0.00212  -0.0022   0.4242   1.0000
   2.000   0.2690   0.00942   0.00219  -0.0016   0.3977   1.0000
   2.250   0.2944   0.00961   0.00228  -0.0011   0.3738   1.0000
   2.500   0.3200   0.00982   0.00240  -0.0006   0.3514   1.0000
   2.750   0.3458   0.01003   0.00253  -0.0001   0.3292   1.0000
   3.000   0.3717   0.01025   0.00267   0.0003   0.3092   1.0000
   3.250   0.3977   0.01048   0.00284   0.0007   0.2885   1.0000
   3.500   0.4237   0.01074   0.00303   0.0011   0.2679   1.0000
   3.750   0.4497   0.01099   0.00323   0.0014   0.2476   1.0000
   4.000   0.4758   0.01126   0.00345   0.0018   0.2279   1.0000
   4.250   0.5018   0.01156   0.00371   0.0021   0.2103   1.0000
   4.500   0.5280   0.01184   0.00398   0.0025   0.1939   1.0000
   4.750   0.5540   0.01216   0.00427   0.0028   0.1773   1.0000
   5.000   0.5800   0.01249   0.00459   0.0031   0.1620   1.0000
   5.250   0.6060   0.01284   0.00496   0.0035   0.1481   1.0000
   5.500   0.6319   0.01322   0.00533   0.0038   0.1332   1.0000
   5.750   0.6576   0.01363   0.00572   0.0041   0.1184   1.0000
   6.000   0.6832   0.01407   0.00615   0.0044   0.1049   1.0000
   6.250   0.7087   0.01452   0.00665   0.0048   0.0928   1.0000
   6.500   0.7340   0.01501   0.00716   0.0051   0.0815   1.0000
   6.750   0.7591   0.01556   0.00773   0.0055   0.0721   1.0000
   7.000   0.7839   0.01616   0.00835   0.0059   0.0637   1.0000
   7.250   0.8087   0.01675   0.00904   0.0063   0.0565   1.0000
   7.500   0.8327   0.01750   0.00983   0.0067   0.0498   1.0000
   7.750   0.8570   0.01817   0.01064   0.0072   0.0449   1.0000
   8.000   0.8801   0.01905   0.01158   0.0076   0.0407   1.0000
   8.250   0.9031   0.01996   0.01262   0.0082   0.0376   1.0000
   8.500   0.9263   0.02076   0.01357   0.0087   0.0342   1.0000
   8.750   0.9485   0.02172   0.01463   0.0092   0.0316   1.0000
   9.000   0.9685   0.02307   0.01608   0.0099   0.0293   1.0000
   9.250   0.9906   0.02399   0.01724   0.0104   0.0269   1.0000
   9.500   1.0123   0.02483   0.01822   0.0108   0.0241   1.0000
   9.750   1.0300   0.02627   0.01972   0.0114   0.0215   1.0000
  10.000   1.0505   0.02729   0.02101   0.0120   0.0195   1.0000
  10.250   1.0691   0.02848   0.02237   0.0125   0.0175   1.0000
  10.500   1.0852   0.02991   0.02395   0.0131   0.0160   1.0000
  10.750   1.0956   0.03206   0.02629   0.0140   0.0148   1.0000
  11.000   1.1057   0.03416   0.02868   0.0148   0.0138   1.0000
  11.250   1.1122   0.03640   0.03121   0.0157   0.0128   1.0000
  11.500   1.1154   0.03867   0.03369   0.0164   0.0121   1.0000
  11.750   1.1115   0.04101   0.03619   0.0174   0.0116   1.0000
  12.000   1.1027   0.04432   0.03965   0.0165   0.0113   1.0000
  12.250   1.0913   0.04909   0.04461   0.0132   0.0112   1.0000
  12.500   1.0782   0.05514   0.05084   0.0085   0.0111   1.0000
  12.750   1.0601   0.06257   0.05848   0.0030   0.0113   1.0000
  13.000   1.0416   0.07039   0.06644  -0.0026   0.0112   1.0000
  13.250   1.0112   0.08070   0.07697  -0.0092   0.0117   1.0000
  13.500   0.9780   0.09209   0.08850  -0.0163   0.0121   1.0000
  13.750   0.9326   0.10692   0.10349  -0.0251   0.0131   1.0000
  14.000   0.8861   0.12332   0.11995  -0.0340   0.0141   1.0000
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