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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 100,000
Max Cl/Cd: 34.93 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stf86361-il-100000-n5.txt
Download as CSV file: xf-stf86361-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STF 863-615 AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3228   0.13082   0.12565  -0.0886   0.9538   0.0559
 -12.000  -0.3322   0.12730   0.12218  -0.0917   0.9520   0.0564
 -11.750  -0.3408   0.12340   0.11832  -0.0945   0.9506   0.0566
 -11.500  -0.3154   0.12017   0.11505  -0.0887   0.9507   0.0599
 -11.250  -0.3114   0.11739   0.11227  -0.0887   0.9499   0.0625
 -10.250  -0.3774   0.10312   0.09825  -0.0940   0.9412   0.0701
  -9.750  -0.3669   0.09701   0.09221  -0.0902   0.9389   0.0742
  -9.250  -0.3127   0.08301   0.07856  -0.0846   0.9268   0.0782
  -7.750  -0.4849   0.06293   0.05691  -0.0872   0.9149   0.0327
  -7.500  -0.4764   0.05907   0.05290  -0.0871   0.9131   0.0307
  -7.250  -0.4588   0.05428   0.04735  -0.0874   0.9112   0.0256
  -7.000  -0.4368   0.05089   0.04349  -0.0887   0.9098   0.0257
  -6.750  -0.4116   0.04749   0.03960  -0.0905   0.9087   0.0271
  -6.500  -0.3955   0.04533   0.03726  -0.0899   0.9067   0.0279
  -6.250  -0.3736   0.04318   0.03449  -0.0891   0.9045   0.0269
  -6.000  -0.3487   0.04149   0.03242  -0.0890   0.9025   0.0266
  -5.750  -0.3222   0.03975   0.03035  -0.0891   0.9009   0.0265
  -5.500  -0.2953   0.03799   0.02837  -0.0892   0.8996   0.0268
  -5.250  -0.2683   0.03651   0.02685  -0.0896   0.8983   0.0285
  -5.000  -0.2396   0.03557   0.02582  -0.0902   0.8970   0.0309
  -4.750  -0.2101   0.03461   0.02476  -0.0905   0.8959   0.0316
  -4.500  -0.1836   0.03386   0.02396  -0.0905   0.8944   0.0322
  -4.250  -0.1677   0.03328   0.02332  -0.0887   0.8908   0.0328
  -4.000  -0.1424   0.03276   0.02274  -0.0889   0.8883   0.0340
  -3.750  -0.1132   0.03221   0.02215  -0.0901   0.8864   0.0377
  -3.500  -0.0819   0.03194   0.02174  -0.0914   0.8846   0.0398
  -3.250  -0.0488   0.03178   0.02141  -0.0929   0.8831   0.0419
  -3.000  -0.0141   0.03168   0.02117  -0.0948   0.8818   0.0456
  -2.750   0.0045   0.03162   0.02108  -0.0939   0.8774   0.0531
  -2.250   0.0638   0.03151   0.02326  -0.0960   0.8722   0.6615
  -2.000   0.0888   0.03209   0.02371  -0.0948   0.8695   0.6786
  -1.750   0.1230   0.03239   0.02384  -0.0963   0.8678   0.6885
  -1.500   0.1314   0.03269   0.02412  -0.0927   0.8609   0.6944
  -1.250   0.1523   0.03313   0.02453  -0.0909   0.8574   0.7095
  -1.000   0.1768   0.03350   0.02484  -0.0897   0.8550   0.7230
  -0.750   0.1906   0.03388   0.02522  -0.0869   0.8504   0.7356
  -0.500   0.2037   0.03421   0.02557  -0.0838   0.8454   0.7494
  -0.250   0.2324   0.03437   0.02567  -0.0843   0.8426   0.7555
   0.000   0.2678   0.03447   0.02568  -0.0866   0.8407   0.7571
   0.250   0.2890   0.03473   0.02589  -0.0866   0.8353   0.7586
   0.500   0.3138   0.03491   0.02605  -0.0869   0.8311   0.7598
   0.750   0.3447   0.03501   0.02613  -0.0881   0.8284   0.7610
   1.000   0.3788   0.03508   0.02619  -0.0899   0.8264   0.7618
   1.250   0.3935   0.03537   0.02651  -0.0885   0.8188   0.7630
   1.500   0.4245   0.03541   0.02656  -0.0897   0.8152   0.7643
   1.750   0.4605   0.03534   0.02652  -0.0917   0.8127   0.7655
   2.000   0.4775   0.03550   0.02672  -0.0906   0.8037   0.7665
   2.250   0.5124   0.03538   0.02664  -0.0924   0.8004   0.7674
   2.500   0.5329   0.03555   0.02687  -0.0920   0.7927   0.7685
   2.750   0.5636   0.03555   0.02696  -0.0931   0.7884   0.7698
   3.000   0.5985   0.03549   0.02698  -0.0950   0.7859   0.7711
   3.250   0.6142   0.03589   0.02747  -0.0939   0.7767   0.7722
   3.750   0.6646   0.03619   0.02802  -0.0945   0.7649   0.7739
   4.000   0.6962   0.03604   0.02802  -0.0955   0.7608   0.7747
   4.250   0.7157   0.03620   0.02832  -0.0947   0.7515   0.7755
   4.500   0.7497   0.03576   0.02808  -0.0959   0.7469   0.7766
   4.750   0.7696   0.03583   0.02831  -0.0950   0.7364   0.7779
   5.000   0.8069   0.03508   0.02778  -0.0964   0.7321   0.7792
   5.250   0.8282   0.03495   0.02783  -0.0955   0.7201   0.7804
   5.500   0.8555   0.03413   0.02725  -0.0950   0.7065   0.7815
   5.750   0.8784   0.03295   0.02624  -0.0932   0.6825   0.7827
   6.000   0.9077   0.03108   0.02446  -0.0916   0.6386   0.7838
   6.250   0.9617   0.02753   0.01914  -0.0910   0.3633   0.7848
   6.500   0.9590   0.02959   0.02025  -0.0870   0.2203   0.7858
   6.750   0.9593   0.03180   0.02155  -0.0838   0.0850   0.7868
   7.000   0.9680   0.03336   0.02281  -0.0815   0.0464   0.7878
   7.250   0.9804   0.03455   0.02404  -0.0797   0.0385   0.7889
   7.500   0.9937   0.03566   0.02531  -0.0780   0.0348   0.7903
   7.750   1.0053   0.03690   0.02669  -0.0762   0.0324   0.7917
   8.000   1.0132   0.03846   0.02838  -0.0739   0.0306   0.7931
   8.250   1.0236   0.03987   0.02994  -0.0720   0.0296   0.7946
   8.500   1.0353   0.04125   0.03151  -0.0702   0.0283   0.7960
   8.750   1.0486   0.04259   0.03299  -0.0688   0.0263   0.7973
   9.000   1.0626   0.04397   0.03446  -0.0675   0.0245   0.7987
   9.250   1.0792   0.04548   0.03605  -0.0665   0.0234   0.8002
   9.750   1.1390   0.04929   0.04008  -0.0669   0.0217   0.8031
  10.000   1.1632   0.05117   0.04232  -0.0664   0.0208   0.8047
  10.250   1.1801   0.05321   0.04473  -0.0652   0.0193   0.8063
  10.500   1.1953   0.05570   0.04756  -0.0640   0.0184   0.8081
  10.750   1.2060   0.05863   0.05087  -0.0623   0.0180   0.8099
  11.000   1.2101   0.06177   0.05439  -0.0600   0.0177   0.8117
  11.250   1.2085   0.06508   0.05807  -0.0573   0.0175   0.8135
  11.500   1.2022   0.06857   0.06194  -0.0545   0.0174   0.8154
  11.750   1.1919   0.07218   0.06591  -0.0515   0.0173   0.8171
  12.000   1.1784   0.07602   0.07008  -0.0487   0.0173   0.8189
  12.250   1.1624   0.08009   0.07447  -0.0463   0.0173   0.8208
  12.500   1.1447   0.08438   0.07904  -0.0443   0.0173   0.8227
  12.750   1.1252   0.08906   0.08401  -0.0430   0.0173   0.8245
  13.000   1.1045   0.09412   0.08933  -0.0424   0.0173   0.8264
  13.250   1.0823   0.09988   0.09534  -0.0428   0.0174   0.8283
  13.750   1.0357   0.11364   0.10954  -0.0472   0.0178   0.8316
  14.000   1.0120   0.12203   0.11814  -0.0516   0.0181   0.8332
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