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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 50,000
Max Cl/Cd: 22.2 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stf86361-il-50000.txt
Download as CSV file: xf-stf86361-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4863   0.13380   0.12771  -0.0150   1.0019   0.3028
  -9.250  -0.5190   0.13429   0.12834  -0.0136   1.0019   0.3163
  -9.000  -0.5021   0.13026   0.12429  -0.0115   1.0019   0.3354
  -8.750  -0.4884   0.12655   0.12057  -0.0095   1.0019   0.3536
  -8.500  -0.4816   0.12349   0.11753  -0.0075   1.0019   0.3720
  -8.250  -0.4822   0.12126   0.11533  -0.0052   1.0019   0.3937
  -8.000  -0.4926   0.11996   0.11411  -0.0022   1.0019   0.4164
  -7.750  -0.4702   0.11586   0.10999  -0.0005   1.0019   0.4419
  -7.500  -0.4566   0.11292   0.10704   0.0014   1.0019   0.4663
  -7.250  -0.4520   0.11038   0.10453   0.0035   1.0019   0.4873
  -7.000  -0.4492   0.10766   0.10183   0.0053   1.0019   0.5032
  -6.000  -0.5243   0.08968   0.08472   0.0021   1.0019   0.3648
  -5.750  -0.6517   0.07716   0.07186  -0.0171   1.0019   0.3372
  -5.500  -0.5704   0.05571   0.04752  -0.0509   1.0019   0.1395
  -5.250  -0.5400   0.05165   0.04290  -0.0522   1.0019   0.1249
  -5.000  -0.5067   0.04864   0.03903  -0.0536   1.0019   0.1165
  -4.750  -0.4793   0.04596   0.03604  -0.0539   1.0019   0.1135
  -4.500  -0.4477   0.04404   0.03331  -0.0539   1.0019   0.1070
  -4.250  -0.4225   0.04210   0.03123  -0.0531   1.0019   0.1049
  -4.000  -0.3979   0.04065   0.02958  -0.0518   1.0019   0.1034
  -3.750  -0.3757   0.03962   0.02839  -0.0497   1.0019   0.1036
  -3.500  -0.3549   0.03901   0.02761  -0.0474   1.0019   0.1071
  -3.250  -0.3369   0.03838   0.02710  -0.0446   1.0019   0.1119
  -3.000  -0.3158   0.03795   0.02657  -0.0427   1.0019   0.1159
  -2.750  -0.2918   0.03735   0.02598  -0.0422   1.0019   0.1225
  -2.500  -0.2612   0.03674   0.02537  -0.0437   1.0019   0.1382
  -2.250  -0.2295   0.03559   0.02708  -0.0445   1.0019   0.6113
  -2.000  -0.2349   0.03760   0.02897  -0.0339   1.0019   0.7305
  -1.750  -0.2497   0.03821   0.02958  -0.0216   1.0019   0.7822
  -1.500  -0.2639   0.03815   0.02949  -0.0101   1.0019   0.8254
  -1.250  -0.2749   0.03778   0.02903   0.0000   1.0019   0.8682
  -1.000  -0.1391   0.04043   0.03079  -0.0135   1.0019   0.9981
  -0.750  -0.1328   0.04016   0.03039  -0.0113   1.0019   0.9981
  -0.500  -0.1267   0.03990   0.03001  -0.0092   1.0019   0.9981
  -0.250  -0.1206   0.03965   0.02961  -0.0071   1.0019   0.9981
   0.000  -0.1146   0.03940   0.02926  -0.0049   1.0019   0.9981
   0.250  -0.1085   0.03916   0.02894  -0.0029   1.0019   0.9981
   0.500  -0.1021   0.03894   0.02864  -0.0009   1.0019   0.9981
   0.750  -0.0955   0.03874   0.02837   0.0010   1.0019   0.9981
   1.000  -0.0873   0.03862   0.02819   0.0026   1.0019   0.9981
   1.250  -0.0762   0.03866   0.02816   0.0035   1.0019   0.9981
   1.500  -0.0619   0.03888   0.02828   0.0038   1.0019   0.9981
   1.750  -0.0449   0.03926   0.02860   0.0036   1.0019   0.9981
   2.000  -0.0258   0.03981   0.02909   0.0029   1.0019   0.9981
   2.250  -0.0053   0.04048   0.02972   0.0019   1.0019   0.9981
   2.500   0.0164   0.04127   0.03048   0.0006   1.0019   0.9981
   2.750   0.0387   0.04216   0.03136  -0.0008   1.0019   0.9981
   3.000   0.0614   0.04315   0.03234  -0.0024   1.0019   0.9981
   3.250   0.0843   0.04422   0.03342  -0.0041   1.0019   0.9981
   3.500   0.1073   0.04538   0.03460  -0.0058   1.0019   0.9981
   3.750   0.1301   0.04662   0.03587  -0.0077   1.0019   0.9981
   4.000   0.1527   0.04794   0.03724  -0.0095   1.0019   0.9981
   4.250   0.1750   0.04935   0.03871  -0.0114   1.0019   0.9981
   4.500   0.1970   0.05083   0.04026  -0.0133   1.0019   0.9981
   4.750   0.2211   0.05255   0.04211  -0.0158   1.0003   0.9981
   5.000   0.2637   0.05565   0.04531  -0.0218   0.9910   0.9981
   5.250   0.2984   0.05827   0.04805  -0.0264   0.9800   0.9981
   5.500   0.3304   0.06064   0.05057  -0.0305   0.9669   0.9981
   5.750   0.3674   0.06357   0.05366  -0.0354   0.9547   0.9981
   6.000   0.3888   0.06529   0.05560  -0.0374   0.9407   0.9981
   6.250   0.4190   0.06749   0.05799  -0.0409   0.9227   0.9981
   6.500   0.4539   0.07014   0.06085  -0.0451   0.9040   0.9981
   6.750   0.5360   0.07001   0.06110  -0.0523   0.8248   0.9981
   7.000   0.5823   0.07044   0.06184  -0.0558   0.7935   0.9981
   7.250   0.6219   0.07080   0.06252  -0.0585   0.7670   0.9981
   7.500   0.6565   0.07107   0.06311  -0.0603   0.7409   0.9981
   7.750   0.7140   0.07053   0.06308  -0.0641   0.7147   0.9981
   8.000   0.7730   0.06859   0.06172  -0.0666   0.6848   0.9981
   8.250   0.8956   0.04034   0.03193  -0.0440   0.2281   0.9981
   8.500   0.8851   0.04412   0.03466  -0.0403   0.1567   0.9981
   8.750   0.8991   0.04634   0.03650  -0.0385   0.1266   0.9981
   9.000   0.9946   0.04683   0.03665  -0.0434   0.0972   0.9981
   9.250   1.1778   0.05396   0.04400  -0.0623   0.0826   0.9981
   9.500   1.2036   0.05800   0.04875  -0.0619   0.0817   0.9981
   9.750   1.2335   0.06314   0.05447  -0.0624   0.0829   0.9981
  10.000   1.2215   0.06610   0.05816  -0.0569   0.0851   0.9981
  10.250   1.2176   0.07016   0.06273  -0.0534   0.0875   0.9981
  10.500   1.2386   0.07626   0.06911  -0.0536   0.0905   0.9981
  10.750   1.1995   0.07814   0.07154  -0.0462   0.0923   0.9981
  11.000   1.1720   0.08181   0.07562  -0.0415   0.0945   0.9981
  11.250   1.1565   0.08632   0.08040  -0.0388   0.0970   0.9981
  11.500   1.1432   0.09103   0.08537  -0.0367   0.1000   0.9981
  11.750   1.1035   0.09511   0.08974  -0.0337   0.1010   0.9981
  12.000   1.0662   0.10021   0.09506  -0.0324   0.1022   0.9981
  12.250   1.0308   0.10619   0.10122  -0.0329   0.1035   0.9981
  12.500   1.0009   0.11307   0.10821  -0.0350   0.1054   0.9981
  12.750   0.9831   0.12047   0.11570  -0.0379   0.1095   0.9981
  13.000   0.9276   0.13394   0.12915  -0.0484   0.1133   0.9981
  13.250   0.9078   0.14673   0.14186  -0.0573   0.1267   0.9981
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