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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 100,000
Max Cl/Cd: 37.18 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8025-il-100000-n5.txt
Download as CSV file: xf-s8025-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6969   0.08994   0.08515   0.0133   1.0000   0.0181
  -9.500  -0.7065   0.08253   0.07779   0.0089   1.0000   0.0178
  -9.250  -0.7201   0.07329   0.06858   0.0022   1.0000   0.0174
  -9.000  -0.7407   0.06428   0.05950  -0.0065   1.0000   0.0170
  -8.750  -0.7587   0.05823   0.05328  -0.0099   1.0000   0.0166
  -8.500  -0.7697   0.05228   0.04698  -0.0119   1.0000   0.0165
  -8.250  -0.7721   0.04702   0.04130  -0.0128   1.0000   0.0165
  -8.000  -0.7680   0.04222   0.03598  -0.0128   1.0000   0.0167
  -7.750  -0.7580   0.03798   0.03120  -0.0124   1.0000   0.0169
  -7.500  -0.7433   0.03440   0.02710  -0.0118   1.0000   0.0171
  -7.250  -0.7253   0.03131   0.02353  -0.0110   1.0000   0.0176
  -7.000  -0.7049   0.02876   0.02056  -0.0102   1.0000   0.0183
  -6.750  -0.6830   0.02662   0.01808  -0.0093   1.0000   0.0190
  -6.500  -0.6622   0.02454   0.01586  -0.0085   1.0000   0.0202
  -6.250  -0.6396   0.02321   0.01439  -0.0079   1.0000   0.0229
  -6.000  -0.6159   0.02196   0.01293  -0.0071   1.0000   0.0267
  -5.750  -0.5936   0.02048   0.01141  -0.0064   1.0000   0.0316
  -5.500  -0.5701   0.01926   0.01014  -0.0057   1.0000   0.0423
  -5.250  -0.5465   0.01806   0.00898  -0.0050   1.0000   0.0627
  -5.000  -0.5223   0.01716   0.00818  -0.0045   1.0000   0.0915
  -4.750  -0.4976   0.01643   0.00749  -0.0041   1.0000   0.1218
  -4.500  -0.4728   0.01577   0.00688  -0.0036   1.0000   0.1521
  -4.250  -0.4479   0.01514   0.00632  -0.0031   1.0000   0.1824
  -4.000  -0.4231   0.01455   0.00584  -0.0026   1.0000   0.2177
  -3.750  -0.3981   0.01402   0.00540  -0.0020   1.0000   0.2562
  -3.500  -0.3734   0.01351   0.00501  -0.0015   1.0000   0.3022
  -3.250  -0.3489   0.01301   0.00470  -0.0008   1.0000   0.3553
  -3.000  -0.3246   0.01256   0.00444  -0.0001   1.0000   0.4114
  -2.750  -0.3004   0.01214   0.00423   0.0008   1.0000   0.4686
  -2.500  -0.2763   0.01177   0.00405   0.0017   1.0000   0.5271
  -2.250  -0.2523   0.01145   0.00391   0.0028   1.0000   0.5852
  -2.000  -0.2287   0.01116   0.00381   0.0040   1.0000   0.6411
  -1.750  -0.2054   0.01091   0.00373   0.0054   1.0000   0.6958
  -1.500  -0.1822   0.01068   0.00366   0.0069   1.0000   0.7494
  -1.250  -0.1582   0.01049   0.00362   0.0083   1.0000   0.8028
  -1.000  -0.1297   0.01036   0.00361   0.0088   1.0000   0.8588
  -0.750  -0.0894   0.01028   0.00358   0.0068   1.0000   0.9159
  -0.500  -0.0313   0.01026   0.00353   0.0007   0.9711   0.9599
  -0.250   0.0316   0.01028   0.00345  -0.0063   0.9138   0.9887
   0.000   0.0802   0.01035   0.00334  -0.0101   0.8425   1.0000
   0.250   0.1064   0.01051   0.00324  -0.0092   0.7800   1.0000
   0.500   0.1292   0.01071   0.00319  -0.0078   0.7282   1.0000
   0.750   0.1521   0.01091   0.00317  -0.0065   0.6832   1.0000
   1.000   0.1756   0.01112   0.00318  -0.0054   0.6418   1.0000
   1.250   0.1994   0.01133   0.00321  -0.0044   0.6035   1.0000
   1.500   0.2236   0.01156   0.00327  -0.0034   0.5681   1.0000
   1.750   0.2484   0.01179   0.00335  -0.0027   0.5341   1.0000
   2.000   0.2732   0.01203   0.00344  -0.0020   0.5015   1.0000
   2.250   0.2981   0.01229   0.00356  -0.0013   0.4702   1.0000
   2.500   0.3232   0.01257   0.00373  -0.0006   0.4401   1.0000
   2.750   0.3484   0.01285   0.00389   0.0000   0.4116   1.0000
   3.000   0.3738   0.01314   0.00409   0.0005   0.3850   1.0000
   3.250   0.3992   0.01345   0.00432   0.0011   0.3598   1.0000
   3.500   0.4246   0.01377   0.00460   0.0016   0.3365   1.0000
   3.750   0.4502   0.01411   0.00488   0.0020   0.3133   1.0000
   4.000   0.4758   0.01446   0.00520   0.0025   0.2915   1.0000
   4.250   0.5012   0.01484   0.00556   0.0029   0.2695   1.0000
   4.500   0.5267   0.01523   0.00593   0.0034   0.2487   1.0000
   4.750   0.5522   0.01565   0.00633   0.0038   0.2281   1.0000
   5.000   0.5775   0.01610   0.00676   0.0042   0.2094   1.0000
   5.250   0.6029   0.01657   0.00728   0.0046   0.1914   1.0000
   5.500   0.6281   0.01708   0.00782   0.0050   0.1742   1.0000
   5.750   0.6530   0.01764   0.00839   0.0054   0.1578   1.0000
   6.000   0.6778   0.01824   0.00903   0.0058   0.1431   1.0000
   6.250   0.7023   0.01889   0.00969   0.0062   0.1281   1.0000
   6.750   0.7506   0.02035   0.01126   0.0070   0.1012   1.0000
   7.000   0.7745   0.02116   0.01221   0.0075   0.0902   1.0000
   7.250   0.7980   0.02207   0.01322   0.0080   0.0801   1.0000
   7.500   0.8207   0.02307   0.01430   0.0085   0.0717   1.0000
   7.750   0.8431   0.02417   0.01557   0.0091   0.0652   1.0000
   8.000   0.8645   0.02550   0.01703   0.0098   0.0597   1.0000
   8.250   0.8862   0.02667   0.01837   0.0103   0.0539   1.0000
   8.500   0.9058   0.02825   0.02001   0.0109   0.0501   1.0000
   8.750   0.9260   0.03004   0.02216   0.0117   0.0469   1.0000
   9.000   0.9450   0.03169   0.02405   0.0123   0.0433   1.0000
   9.250   0.9625   0.03326   0.02567   0.0129   0.0402   1.0000
   9.500   0.9774   0.03578   0.02861   0.0136   0.0379   1.0000
   9.750   0.9898   0.03846   0.03174   0.0143   0.0355   1.0000
  10.000   1.0014   0.04055   0.03410   0.0148   0.0328   1.0000
  10.250   1.0122   0.04241   0.03604   0.0153   0.0307   1.0000
  10.500   1.0139   0.04578   0.03965   0.0157   0.0294   1.0000
  10.750   1.0071   0.04963   0.04396   0.0159   0.0284   1.0000
  11.000   0.9918   0.05364   0.04826   0.0157   0.0279   1.0000
  11.250   0.9726   0.05884   0.05369   0.0126   0.0278   1.0000
  11.500   0.9520   0.06573   0.06075   0.0070   0.0283   1.0000
  11.750   0.9289   0.07426   0.06941   0.0000   0.0288   1.0000
  12.000   0.9050   0.08361   0.07883  -0.0069   0.0294   1.0000
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