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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 500,000
Max Cl/Cd: 65.14 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8025-il-500000-n5.txt
Download as CSV file: xf-s8025-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.8789   0.05170   0.04919  -0.0096   1.0000   0.0035
 -10.250  -0.9003   0.04587   0.04317  -0.0142   1.0000   0.0035
 -10.000  -0.9186   0.04113   0.03814  -0.0142   1.0000   0.0034
  -9.750  -0.9236   0.03684   0.03350  -0.0139   1.0000   0.0034
  -9.500  -0.9221   0.03279   0.02903  -0.0133   1.0000   0.0034
  -9.250  -0.9134   0.02951   0.02536  -0.0124   1.0000   0.0034
  -9.000  -0.9002   0.02678   0.02226  -0.0116   1.0000   0.0034
  -8.750  -0.8835   0.02456   0.01974  -0.0107   1.0000   0.0034
  -8.500  -0.8649   0.02263   0.01753  -0.0099   1.0000   0.0035
  -8.250  -0.8445   0.02103   0.01570  -0.0092   1.0000   0.0035
  -8.000  -0.8231   0.01961   0.01407  -0.0084   1.0000   0.0036
  -7.750  -0.8008   0.01836   0.01264  -0.0077   1.0000   0.0037
  -7.500  -0.7777   0.01728   0.01139  -0.0071   1.0000   0.0037
  -7.250  -0.7542   0.01630   0.01027  -0.0065   1.0000   0.0039
  -7.000  -0.7300   0.01546   0.00931  -0.0059   1.0000   0.0040
  -6.750  -0.7054   0.01473   0.00848  -0.0054   1.0000   0.0041
  -6.500  -0.6814   0.01378   0.00743  -0.0048   1.0000   0.0044
  -6.250  -0.6562   0.01314   0.00672  -0.0043   1.0000   0.0048
  -6.000  -0.6307   0.01262   0.00611  -0.0039   1.0000   0.0052
  -5.750  -0.6049   0.01213   0.00556  -0.0034   1.0000   0.0058
  -5.500  -0.5788   0.01170   0.00506  -0.0030   1.0000   0.0063
  -5.250  -0.5531   0.01121   0.00453  -0.0026   1.0000   0.0078
  -5.000  -0.5272   0.01077   0.00408  -0.0021   1.0000   0.0110
  -4.750  -0.5015   0.01027   0.00362  -0.0016   1.0000   0.0210
  -4.500  -0.4758   0.00982   0.00328  -0.0012   1.0000   0.0390
  -4.250  -0.4499   0.00947   0.00300  -0.0008   1.0000   0.0558
  -4.000  -0.4243   0.00906   0.00274  -0.0004   1.0000   0.0847
  -3.750  -0.3984   0.00873   0.00252   0.0000   1.0000   0.1097
  -3.500  -0.3725   0.00842   0.00231   0.0004   1.0000   0.1345
  -3.250  -0.3466   0.00816   0.00214   0.0008   1.0000   0.1584
  -3.000  -0.3121   0.00793   0.00197  -0.0006   0.9810   0.1824
  -2.750  -0.2691   0.00768   0.00180  -0.0039   0.9358   0.2163
  -2.500  -0.2371   0.00756   0.00165  -0.0044   0.8708   0.2490
  -2.250  -0.2127   0.00756   0.00153  -0.0034   0.8110   0.2756
  -2.000  -0.1878   0.00751   0.00142  -0.0026   0.7626   0.3122
  -1.750  -0.1623   0.00741   0.00131  -0.0020   0.7224   0.3576
  -1.500  -0.1364   0.00734   0.00123  -0.0015   0.6830   0.3998
  -1.250  -0.1101   0.00731   0.00116  -0.0011   0.6446   0.4354
  -1.000  -0.0838   0.00725   0.00110  -0.0007   0.6089   0.4757
  -0.750  -0.0574   0.00718   0.00106  -0.0003   0.5756   0.5224
  -0.500  -0.0309   0.00713   0.00104   0.0001   0.5457   0.5655
  -0.250  -0.0044   0.00707   0.00103   0.0005   0.5191   0.6072
   0.000   0.0222   0.00704   0.00102   0.0009   0.4922   0.6461
   0.250   0.0487   0.00702   0.00103   0.0013   0.4664   0.6817
   0.500   0.0752   0.00701   0.00105   0.0018   0.4419   0.7165
   0.750   0.1011   0.00700   0.00108   0.0023   0.4144   0.7569
   1.000   0.1265   0.00697   0.00112   0.0031   0.3880   0.8022
   1.250   0.1516   0.00695   0.00117   0.0040   0.3662   0.8487
   1.500   0.1775   0.00694   0.00123   0.0047   0.3471   0.8957
   1.750   0.2102   0.00703   0.00130   0.0040   0.3249   0.9386
   2.000   0.2508   0.00715   0.00137   0.0013   0.3035   0.9707
   2.250   0.2883   0.00730   0.00144  -0.0007   0.2840   0.9921
   2.500   0.3208   0.00747   0.00152  -0.0017   0.2645   1.0000
   2.750   0.3467   0.00763   0.00162  -0.0012   0.2459   1.0000
   3.000   0.3726   0.00783   0.00172  -0.0008   0.2259   1.0000
   3.250   0.3988   0.00801   0.00185  -0.0004   0.2096   1.0000
   3.500   0.4251   0.00819   0.00198   0.0000   0.1952   1.0000
   3.750   0.4514   0.00840   0.00212   0.0003   0.1795   1.0000
   4.000   0.4778   0.00860   0.00228   0.0007   0.1660   1.0000
   4.250   0.5043   0.00882   0.00247   0.0010   0.1540   1.0000
   4.500   0.5307   0.00904   0.00266   0.0013   0.1419   1.0000
   5.000   0.5835   0.00956   0.00309   0.0019   0.1137   1.0000
   5.250   0.6098   0.00985   0.00334   0.0022   0.1008   1.0000
   5.500   0.6361   0.01014   0.00360   0.0025   0.0890   1.0000
   5.750   0.6625   0.01041   0.00388   0.0028   0.0797   1.0000
   6.000   0.6887   0.01073   0.00418   0.0031   0.0704   1.0000
   6.250   0.7148   0.01109   0.00452   0.0034   0.0613   1.0000
   6.500   0.7409   0.01143   0.00487   0.0037   0.0541   1.0000
   6.750   0.7669   0.01178   0.00524   0.0040   0.0483   1.0000
   7.000   0.7928   0.01217   0.00564   0.0043   0.0422   1.0000
   7.250   0.8186   0.01257   0.00608   0.0047   0.0375   1.0000
   7.500   0.8441   0.01301   0.00654   0.0050   0.0327   1.0000
   7.750   0.8694   0.01349   0.00707   0.0053   0.0289   1.0000
   8.000   0.8949   0.01393   0.00756   0.0057   0.0262   1.0000
   8.250   0.9197   0.01447   0.00811   0.0060   0.0230   1.0000
   8.500   0.9446   0.01499   0.00869   0.0064   0.0207   1.0000
   8.750   0.9695   0.01546   0.00925   0.0067   0.0191   1.0000
   9.000   0.9940   0.01601   0.00988   0.0071   0.0174   1.0000
   9.250   1.0177   0.01669   0.01062   0.0075   0.0157   1.0000
   9.500   1.0417   0.01729   0.01132   0.0079   0.0145   1.0000
   9.750   1.0656   0.01785   0.01197   0.0083   0.0130   1.0000
  10.000   1.0888   0.01852   0.01269   0.0087   0.0113   1.0000
  10.250   1.1115   0.01926   0.01351   0.0092   0.0097   1.0000
  10.500   1.1339   0.02000   0.01435   0.0097   0.0083   1.0000
  10.750   1.1548   0.02098   0.01542   0.0102   0.0071   1.0000
  11.000   1.1755   0.02192   0.01650   0.0108   0.0064   1.0000
  11.250   1.1950   0.02296   0.01767   0.0114   0.0057   1.0000
  11.500   1.2134   0.02412   0.01894   0.0121   0.0052   1.0000
  11.750   1.2285   0.02563   0.02060   0.0129   0.0047   1.0000
  12.000   1.2443   0.02692   0.02206   0.0137   0.0045   1.0000
  12.250   1.2581   0.02834   0.02363   0.0145   0.0042   1.0000
  12.500   1.2700   0.02982   0.02527   0.0154   0.0039   1.0000
  12.750   1.2784   0.03151   0.02712   0.0164   0.0037   1.0000
  13.000   1.2797   0.03352   0.02931   0.0178   0.0036   1.0000
  13.250   1.2737   0.03572   0.03165   0.0193   0.0035   1.0000
  13.500   1.2581   0.03975   0.03587   0.0181   0.0034   1.0000
  13.750   1.2452   0.04520   0.04150   0.0140   0.0034   1.0000
  14.000   1.2217   0.05368   0.05021   0.0073   0.0035   1.0000
  14.250   1.1975   0.06243   0.05913   0.0012   0.0035   1.0000
  14.500   1.1594   0.07358   0.07043  -0.0058   0.0038   1.0000
  14.750   1.1264   0.08383   0.08081  -0.0118   0.0037   1.0000
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