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S8038 (13%) (s8038-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S8038 (13%) (s8038-il)
Reynolds number: 100,000
Max Cl/Cd: 43.23 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8038-il-100000-n5.txt
Download as CSV file: xf-s8038-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8038 (13%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6220   0.09702   0.09146  -0.0327   1.0000   0.0267
 -12.500  -0.6752   0.08100   0.07529  -0.0436   1.0000   0.0258
 -12.250  -0.7140   0.07130   0.06537  -0.0502   1.0000   0.0253
 -12.000  -0.7453   0.06442   0.05824  -0.0538   1.0000   0.0249
 -11.750  -0.7675   0.05958   0.05318  -0.0551   1.0000   0.0250
 -11.500  -0.7861   0.05564   0.04902  -0.0551   1.0000   0.0249
 -11.250  -0.8017   0.05236   0.04551  -0.0540   1.0000   0.0249
 -11.000  -0.8141   0.04963   0.04258  -0.0518   1.0000   0.0250
 -10.750  -0.8245   0.04726   0.04000  -0.0487   1.0000   0.0251
 -10.500  -0.8317   0.04509   0.03763  -0.0453   1.0000   0.0253
 -10.250  -0.8328   0.04290   0.03521  -0.0425   1.0000   0.0256
 -10.000  -0.8303   0.04079   0.03288  -0.0399   1.0000   0.0259
  -9.750  -0.8246   0.03877   0.03063  -0.0374   1.0000   0.0263
  -9.500  -0.8160   0.03686   0.02848  -0.0351   1.0000   0.0268
  -9.250  -0.8051   0.03507   0.02647  -0.0330   1.0000   0.0274
  -9.000  -0.7925   0.03345   0.02464  -0.0310   1.0000   0.0282
  -8.750  -0.7795   0.03200   0.02302  -0.0290   1.0000   0.0293
  -8.500  -0.7667   0.03075   0.02179  -0.0270   1.0000   0.0305
  -8.250  -0.7530   0.02961   0.02059  -0.0251   1.0000   0.0318
  -8.000  -0.7389   0.02845   0.01935  -0.0230   1.0000   0.0331
  -7.750  -0.7250   0.02731   0.01811  -0.0208   1.0000   0.0343
  -7.500  -0.7115   0.02628   0.01697  -0.0185   1.0000   0.0356
  -7.250  -0.7008   0.02519   0.01589  -0.0160   1.0000   0.0371
  -7.000  -0.6888   0.02429   0.01497  -0.0135   1.0000   0.0393
  -6.750  -0.6762   0.02349   0.01411  -0.0111   1.0000   0.0423
  -6.500  -0.6647   0.02264   0.01326  -0.0086   1.0000   0.0464
  -6.250  -0.6522   0.02190   0.01247  -0.0061   1.0000   0.0527
  -6.000  -0.6409   0.02107   0.01169  -0.0035   1.0000   0.0606
  -5.750  -0.6291   0.02034   0.01101  -0.0010   1.0000   0.0734
  -5.500  -0.6011   0.01941   0.01030  -0.0020   0.9947   0.1057
  -5.250  -0.5697   0.01841   0.00968  -0.0037   0.9865   0.1648
  -5.000  -0.5396   0.01751   0.00914  -0.0051   0.9776   0.2364
  -4.750  -0.5092   0.01674   0.00870  -0.0063   0.9686   0.3063
  -4.500  -0.4790   0.01608   0.00836  -0.0072   0.9593   0.3798
  -4.250  -0.4502   0.01560   0.00814  -0.0076   0.9491   0.4462
  -4.000  -0.4177   0.01531   0.00802  -0.0084   0.9408   0.5040
  -3.750  -0.3852   0.01514   0.00792  -0.0090   0.9316   0.5500
  -3.500  -0.3528   0.01502   0.00780  -0.0096   0.9224   0.5859
  -3.250  -0.3164   0.01493   0.00767  -0.0110   0.9148   0.6152
  -3.000  -0.2848   0.01486   0.00754  -0.0114   0.9043   0.6403
  -2.750  -0.2485   0.01479   0.00743  -0.0126   0.8965   0.6618
  -2.500  -0.2169   0.01472   0.00731  -0.0130   0.8856   0.6802
  -2.250  -0.1842   0.01466   0.00719  -0.0136   0.8753   0.6971
  -2.000  -0.1485   0.01459   0.00705  -0.0147   0.8666   0.7131
  -1.750  -0.1183   0.01455   0.00697  -0.0148   0.8546   0.7277
  -1.500  -0.0866   0.01450   0.00687  -0.0152   0.8436   0.7413
  -1.250  -0.0533   0.01444   0.00674  -0.0159   0.8334   0.7544
  -1.000  -0.0240   0.01440   0.00665  -0.0159   0.8211   0.7675
  -0.750   0.0060   0.01438   0.00661  -0.0159   0.8088   0.7790
  -0.500   0.0366   0.01436   0.00655  -0.0161   0.7971   0.7900
  -0.250   0.0674   0.01434   0.00646  -0.0163   0.7859   0.8014
   0.000   0.0959   0.01434   0.00643  -0.0161   0.7733   0.8127
   0.250   0.1255   0.01435   0.00644  -0.0161   0.7608   0.8229
   0.500   0.1545   0.01436   0.00642  -0.0161   0.7485   0.8339
   0.750   0.1838   0.01438   0.00639  -0.0160   0.7364   0.8451
   1.000   0.2155   0.01440   0.00640  -0.0164   0.7239   0.8545
   1.250   0.2444   0.01443   0.00642  -0.0164   0.7099   0.8652
   1.500   0.2742   0.01447   0.00645  -0.0166   0.6957   0.8760
   1.750   0.3065   0.01453   0.00650  -0.0172   0.6812   0.8853
   2.000   0.3374   0.01459   0.00654  -0.0176   0.6662   0.8960
   2.250   0.3702   0.01465   0.00659  -0.0184   0.6498   0.9062
   2.500   0.4044   0.01472   0.00663  -0.0194   0.6315   0.9154
   2.750   0.4369   0.01479   0.00666  -0.0202   0.6124   0.9262
   3.000   0.4724   0.01488   0.00675  -0.0217   0.5909   0.9351
   3.250   0.5075   0.01499   0.00683  -0.0230   0.5693   0.9447
   3.500   0.5416   0.01511   0.00692  -0.0243   0.5465   0.9550
   3.750   0.5781   0.01525   0.00701  -0.0261   0.5210   0.9638
   4.000   0.6122   0.01541   0.00714  -0.0276   0.4929   0.9747
   4.250   0.6462   0.01561   0.00726  -0.0290   0.4622   0.9860
   4.500   0.6808   0.01587   0.00741  -0.0308   0.4270   0.9971
   5.000   0.7111   0.01645   0.00773  -0.0266   0.3659   1.0000
   5.250   0.7238   0.01683   0.00797  -0.0240   0.3356   1.0000
   5.500   0.7373   0.01727   0.00827  -0.0216   0.3063   1.0000
   5.750   0.7511   0.01776   0.00862  -0.0192   0.2786   1.0000
   6.000   0.7653   0.01829   0.00902  -0.0169   0.2541   1.0000
   6.250   0.7798   0.01884   0.00946  -0.0147   0.2321   1.0000
   6.500   0.7942   0.01943   0.00996  -0.0125   0.2130   1.0000
   6.750   0.8091   0.02003   0.01047  -0.0104   0.1967   1.0000
   7.000   0.8244   0.02063   0.01103  -0.0084   0.1833   1.0000
   7.250   0.8402   0.02124   0.01162  -0.0065   0.1713   1.0000
   7.500   0.8558   0.02188   0.01225  -0.0046   0.1608   1.0000
   7.750   0.8704   0.02259   0.01289  -0.0026   0.1519   1.0000
   8.000   0.8867   0.02323   0.01359  -0.0009   0.1434   1.0000
   8.250   0.9014   0.02399   0.01431   0.0010   0.1369   1.0000
   8.500   0.9177   0.02469   0.01509   0.0027   0.1301   1.0000
   8.750   0.9315   0.02551   0.01585   0.0046   0.1246   1.0000
   9.000   0.9479   0.02625   0.01670   0.0062   0.1187   1.0000
   9.250   0.9627   0.02704   0.01753   0.0080   0.1139   1.0000
   9.500   0.9766   0.02797   0.01841   0.0097   0.1098   1.0000
   9.750   0.9916   0.02879   0.01940   0.0114   0.1052   1.0000
  10.000   1.0042   0.02964   0.02030   0.0134   0.1010   1.0000
  10.250   1.0159   0.03061   0.02124   0.0153   0.0976   1.0000
  10.500   1.0295   0.03161   0.02239   0.0170   0.0940   1.0000
  10.750   1.0414   0.03261   0.02353   0.0188   0.0903   1.0000
  11.000   1.0519   0.03362   0.02458   0.0206   0.0871   1.0000
  11.250   1.0633   0.03481   0.02576   0.0221   0.0844   1.0000
  11.500   1.0736   0.03609   0.02727   0.0237   0.0816   1.0000
  11.750   1.0821   0.03740   0.02875   0.0254   0.0785   1.0000
  12.000   1.0899   0.03871   0.03016   0.0269   0.0760   1.0000
  12.250   1.0977   0.04007   0.03157   0.0283   0.0738   1.0000
  12.500   1.1072   0.04166   0.03317   0.0294   0.0719   1.0000
  12.750   1.1102   0.04360   0.03541   0.0308   0.0701   1.0000
  13.000   1.1119   0.04566   0.03771   0.0320   0.0681   1.0000
  13.250   1.1129   0.04777   0.04001   0.0329   0.0662   1.0000
  13.500   1.1136   0.04993   0.04230   0.0336   0.0646   1.0000
  13.750   1.1150   0.05206   0.04451   0.0341   0.0631   1.0000
  14.000   1.1185   0.05414   0.04662   0.0345   0.0617   1.0000
  14.250   1.1168   0.05700   0.04960   0.0347   0.0606   1.0000
  14.500   1.1049   0.06091   0.05380   0.0342   0.0598   1.0000
  14.750   1.0894   0.06546   0.05863   0.0332   0.0590   1.0000
  15.000   1.0706   0.07072   0.06415   0.0314   0.0584   1.0000
  15.250   1.0464   0.07708   0.07076   0.0285   0.0578   1.0000
  15.500   1.0145   0.08520   0.07914   0.0242   0.0577   1.0000
  15.750   0.9606   0.09836   0.09256   0.0161   0.0579   1.0000
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