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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 200,000
Max Cl/Cd: 46.78 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8025-il-200000.txt
Download as CSV file: xf-s8025-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5715   0.12405   0.12081   0.0220   1.0000   0.0471
 -10.750  -0.5740   0.11920   0.11597   0.0193   1.0000   0.0473
  -7.750  -0.7426   0.04384   0.03942  -0.0134   1.0000   0.0244
  -7.500  -0.7461   0.03438   0.02886  -0.0126   1.0000   0.0204
  -7.250  -0.7278   0.03127   0.02515  -0.0115   1.0000   0.0195
  -7.000  -0.7079   0.02860   0.02209  -0.0106   1.0000   0.0193
  -6.750  -0.6877   0.02550   0.01859  -0.0097   1.0000   0.0194
  -6.500  -0.6663   0.02259   0.01536  -0.0087   1.0000   0.0198
  -6.250  -0.6436   0.02093   0.01361  -0.0082   1.0000   0.0219
  -6.000  -0.6190   0.01981   0.01237  -0.0075   1.0000   0.0244
  -5.750  -0.5945   0.01835   0.01075  -0.0066   1.0000   0.0260
  -5.500  -0.5721   0.01644   0.00876  -0.0055   1.0000   0.0286
  -5.250  -0.5478   0.01533   0.00761  -0.0046   1.0000   0.0351
  -5.000  -0.5250   0.01379   0.00623  -0.0037   1.0000   0.0658
  -4.750  -0.5001   0.01304   0.00562  -0.0032   1.0000   0.1077
  -4.500  -0.4747   0.01251   0.00518  -0.0028   1.0000   0.1410
  -4.250  -0.4498   0.01191   0.00474  -0.0024   1.0000   0.1771
  -4.000  -0.4249   0.01133   0.00433  -0.0019   1.0000   0.2195
  -3.750  -0.3999   0.01079   0.00396  -0.0014   1.0000   0.2674
  -3.500  -0.3752   0.01027   0.00364  -0.0008   1.0000   0.3213
  -3.250  -0.3507   0.00980   0.00339  -0.0002   1.0000   0.3815
  -3.000  -0.3265   0.00936   0.00319   0.0006   1.0000   0.4428
  -2.750  -0.3026   0.00896   0.00305   0.0015   1.0000   0.5093
  -2.500  -0.2793   0.00860   0.00293   0.0026   1.0000   0.5770
  -2.250  -0.2561   0.00830   0.00285   0.0039   1.0000   0.6391
  -2.000  -0.2334   0.00802   0.00279   0.0054   1.0000   0.6938
  -1.750  -0.2113   0.00778   0.00275   0.0070   1.0000   0.7470
  -1.500  -0.1901   0.00756   0.00272   0.0090   1.0000   0.8015
  -1.250  -0.1683   0.00740   0.00273   0.0109   1.0000   0.8589
  -1.000  -0.1340   0.00735   0.00277   0.0104   1.0000   0.9193
  -0.750  -0.0795   0.00737   0.00277   0.0053   1.0000   0.9651
  -0.500  -0.0227   0.00738   0.00274  -0.0007   1.0000   0.9936
  -0.250   0.0119   0.00735   0.00269  -0.0026   0.9937   1.0000
   0.000   0.0753   0.00736   0.00263  -0.0098   0.9282   1.0000
   0.250   0.1162   0.00742   0.00250  -0.0118   0.8459   1.0000
   0.500   0.1369   0.00761   0.00241  -0.0098   0.7816   1.0000
   0.750   0.1578   0.00783   0.00237  -0.0080   0.7294   1.0000
   1.000   0.1798   0.00807   0.00236  -0.0066   0.6833   1.0000
   1.250   0.2027   0.00830   0.00237  -0.0053   0.6404   1.0000
   1.500   0.2261   0.00852   0.00241  -0.0043   0.5989   1.0000
   1.750   0.2501   0.00876   0.00245  -0.0033   0.5598   1.0000
   2.000   0.2744   0.00901   0.00251  -0.0025   0.5239   1.0000
   2.250   0.2993   0.00924   0.00261  -0.0018   0.4897   1.0000
   2.500   0.3243   0.00950   0.00273  -0.0011   0.4578   1.0000
   2.750   0.3495   0.00977   0.00287  -0.0005   0.4277   1.0000
   3.000   0.3750   0.01004   0.00302   0.0000   0.3996   1.0000
   3.250   0.4006   0.01032   0.00322   0.0005   0.3722   1.0000
   3.500   0.4262   0.01061   0.00341   0.0010   0.3457   1.0000
   3.750   0.4519   0.01092   0.00362   0.0015   0.3205   1.0000
   4.000   0.4776   0.01124   0.00386   0.0019   0.2964   1.0000
   4.250   0.5035   0.01156   0.00415   0.0023   0.2733   1.0000
   4.500   0.5291   0.01194   0.00444   0.0027   0.2525   1.0000
   4.750   0.5551   0.01228   0.00477   0.0031   0.2306   1.0000
   5.000   0.5806   0.01271   0.00512   0.0035   0.2114   1.0000
   5.250   0.6064   0.01312   0.00555   0.0039   0.1924   1.0000
   5.500   0.6320   0.01356   0.00596   0.0043   0.1735   1.0000
   5.750   0.6571   0.01409   0.00642   0.0047   0.1556   1.0000
   6.000   0.6825   0.01459   0.00694   0.0051   0.1384   1.0000
   6.250   0.7077   0.01514   0.00753   0.0055   0.1226   1.0000
   6.500   0.7326   0.01576   0.00816   0.0059   0.1081   1.0000
   6.750   0.7570   0.01652   0.00894   0.0064   0.0959   1.0000
   7.000   0.7810   0.01739   0.00982   0.0070   0.0848   1.0000
   7.250   0.8042   0.01841   0.01080   0.0075   0.0747   1.0000
   7.500   0.8289   0.01915   0.01171   0.0081   0.0672   1.0000
   7.750   0.8510   0.02072   0.01331   0.0088   0.0616   1.0000
   8.000   0.8748   0.02173   0.01453   0.0094   0.0568   1.0000
   8.250   0.8972   0.02294   0.01575   0.0100   0.0522   1.0000
   8.500   0.9183   0.02504   0.01811   0.0108   0.0492   1.0000
   8.750   0.9402   0.02640   0.01975   0.0115   0.0458   1.0000
   9.000   0.9617   0.02737   0.02079   0.0120   0.0420   1.0000
   9.250   0.9775   0.03021   0.02394   0.0127   0.0387   1.0000
   9.500   0.9970   0.03125   0.02529   0.0134   0.0350   1.0000
   9.750   1.0162   0.03211   0.02618   0.0139   0.0316   1.0000
  10.000   1.0229   0.03610   0.03054   0.0148   0.0292   1.0000
  10.250   1.0308   0.03897   0.03389   0.0158   0.0275   1.0000
  10.500   1.0325   0.04242   0.03775   0.0166   0.0261   1.0000
  10.750   1.0287   0.04604   0.04169   0.0173   0.0252   1.0000
  11.000   1.0159   0.04979   0.04571   0.0179   0.0248   1.0000
  11.250   0.9971   0.05392   0.05004   0.0169   0.0247   1.0000
  11.500   0.9631   0.06221   0.05862   0.0099   0.0259   1.0000
  11.750   0.9320   0.07235   0.06894   0.0009   0.0268   1.0000
  12.000   0.8994   0.08396   0.08063  -0.0081   0.0283   1.0000
  12.250   0.8689   0.09530   0.09198  -0.0153   0.0295   1.0000
  12.500   0.7820   0.12674   0.12328  -0.0306   0.0395   1.0000
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