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S8037 (16%) (s8037-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8037 (16%) (s8037-il)
Reynolds number: 50,000
Max Cl/Cd: 7.18 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8037-il-50000.txt
Download as CSV file: xf-s8037-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8037 (16%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2939   0.10899   0.10236  -0.0295   1.0000   0.3290
  -9.500  -0.3100   0.10714   0.10066  -0.0287   1.0000   0.3390
  -9.250  -0.4074   0.08860   0.08242  -0.0476   1.0000   0.1670
  -9.000  -0.4921   0.08302   0.07711  -0.0491   1.0000   0.1559
  -8.750  -0.5515   0.08330   0.07754  -0.0420   1.0000   0.1567
  -8.500  -0.5521   0.07982   0.07413  -0.0396   1.0000   0.1496
  -8.250  -0.6047   0.07802   0.07236  -0.0342   1.0000   0.1463
  -8.000  -0.6499   0.07511   0.06930  -0.0297   1.0000   0.1393
  -7.750  -0.6663   0.07204   0.06618  -0.0264   1.0000   0.1364
  -7.500  -0.7202   0.06784   0.06126  -0.0207   1.0000   0.1264
  -7.250  -0.7197   0.06458   0.05796  -0.0184   1.0000   0.1250
  -7.000  -0.7237   0.06143   0.05463  -0.0155   1.0000   0.1234
  -6.750  -0.7275   0.05820   0.05114  -0.0126   1.0000   0.1214
  -6.500  -0.7301   0.05492   0.04746  -0.0095   1.0000   0.1190
  -6.250  -0.7292   0.05186   0.04395  -0.0065   1.0000   0.1173
  -6.000  -0.7241   0.04920   0.04087  -0.0037   1.0000   0.1170
  -5.750  -0.7157   0.04700   0.03834  -0.0013   1.0000   0.1189
  -5.500  -0.7056   0.04499   0.03594   0.0010   1.0000   0.1213
  -5.250  -0.6935   0.04304   0.03354   0.0033   1.0000   0.1238
  -5.000  -0.6793   0.04123   0.03122   0.0055   1.0000   0.1262
  -4.750  -0.6625   0.03938   0.02936   0.0068   1.0000   0.1312
  -4.500  -0.6458   0.03809   0.02784   0.0085   1.0000   0.1396
  -4.250  -0.6268   0.03665   0.02636   0.0096   1.0000   0.1474
  -4.000  -0.6061   0.03540   0.02509   0.0107   0.9995   0.1617
  -3.750  -0.5664   0.03436   0.02420   0.0084   0.9924   0.1925
  -3.500  -0.5337   0.03295   0.02328   0.0073   0.9858   0.2556
  -3.250  -0.5212   0.03031   0.02285   0.0104   0.9808   0.4853
  -3.000  -0.5192   0.03068   0.02423   0.0193   0.9758   0.7171
  -2.750  -0.4781   0.03267   0.02625   0.0218   0.9682   0.8320
  -2.500  -0.1878   0.04107   0.03330  -0.0162   0.9539   0.9419
  -2.250  -0.0333   0.04220   0.03378  -0.0407   0.9458   0.9822
  -2.000   0.0423   0.04197   0.03323  -0.0527   0.9380   1.0000
  -1.750   0.0647   0.04191   0.03301  -0.0548   0.9301   1.0000
  -1.500   0.0657   0.04190   0.03290  -0.0531   0.9214   1.0000
  -1.250   0.0892   0.04201   0.03286  -0.0550   0.9135   1.0000
  -1.000   0.0815   0.04209   0.03287  -0.0516   0.9054   1.0000
  -0.750   0.1007   0.04230   0.03296  -0.0526   0.8975   1.0000
  -0.500   0.0901   0.04245   0.03304  -0.0486   0.8900   1.0000
  -0.250   0.0994   0.04271   0.03319  -0.0477   0.8821   1.0000
   0.000   0.0937   0.04295   0.03335  -0.0443   0.8750   1.0000
   0.250   0.0894   0.04319   0.03350  -0.0410   0.8680   1.0000
   0.500   0.1006   0.04372   0.03390  -0.0399   0.8605   1.0000
   0.750   0.0907   0.04409   0.03416  -0.0355   0.8539   1.0000
   1.000   0.1201   0.04499   0.03491  -0.0370   0.8451   1.0000
   1.250   0.1091   0.04553   0.03535  -0.0323   0.8387   1.0000
   1.500   0.1363   0.04653   0.03623  -0.0334   0.8299   1.0000
   1.750   0.1347   0.04732   0.03691  -0.0301   0.8224   1.0000
   2.000   0.1651   0.04843   0.03793  -0.0315   0.8127   1.0000
   2.250   0.1630   0.04930   0.03871  -0.0283   0.8046   1.0000
   2.500   0.1969   0.05053   0.03985  -0.0300   0.7938   1.0000
   2.750   0.1933   0.05147   0.04073  -0.0267   0.7856   1.0000
   3.000   0.2186   0.05268   0.04187  -0.0272   0.7747   1.0000
   3.250   0.2333   0.05378   0.04291  -0.0263   0.7642   1.0000
   3.500   0.2434   0.05497   0.04405  -0.0249   0.7535   1.0000
   3.750   0.2714   0.05620   0.04524  -0.0256   0.7413   1.0000
   4.000   0.2844   0.05740   0.04641  -0.0245   0.7302   1.0000
   4.250   0.2935   0.05868   0.04766  -0.0231   0.7188   1.0000
   4.500   0.3161   0.05988   0.04884  -0.0230   0.7052   1.0000
   4.750   0.3462   0.06103   0.04998  -0.0235   0.6916   1.0000
   5.000   0.3631   0.06219   0.05114  -0.0228   0.6783   1.0000
   5.250   0.3644   0.06371   0.05265  -0.0208   0.6665   1.0000
   5.500   0.3821   0.06500   0.05394  -0.0202   0.6531   1.0000
   5.750   0.4047   0.06620   0.05515  -0.0199   0.6391   1.0000
   6.000   0.4347   0.06721   0.05618  -0.0201   0.6255   1.0000
   6.250   0.4502   0.06846   0.05746  -0.0193   0.6121   1.0000
   6.500   0.4485   0.07039   0.05940  -0.0175   0.5999   1.0000
   6.750   0.4624   0.07183   0.06087  -0.0166   0.5863   1.0000
   7.000   0.4806   0.07320   0.06226  -0.0161   0.5732   1.0000
   7.250   0.5067   0.07422   0.06334  -0.0158   0.5599   1.0000
   7.500   0.5374   0.07489   0.06407  -0.0156   0.5464   1.0000
   7.750   0.5251   0.07768   0.06686  -0.0139   0.5342   1.0000
   8.000   0.5327   0.07958   0.06880  -0.0129   0.5214   1.0000
   8.250   0.5489   0.08112   0.07039  -0.0123   0.5089   1.0000
   8.500   0.5777   0.08189   0.07123  -0.0119   0.4964   1.0000
   8.750   0.5834   0.08401   0.07341  -0.0111   0.4842   1.0000
   9.000   0.5754   0.08728   0.07670  -0.0103   0.4735   1.0000
   9.250   0.5912   0.08895   0.07842  -0.0097   0.4617   1.0000
   9.500   0.6258   0.08920   0.07878  -0.0091   0.4495   1.0000
   9.750   0.5990   0.09425   0.08384  -0.0088   0.4409   1.0000
  10.000   0.6121   0.09627   0.08592  -0.0083   0.4299   1.0000
  10.250   0.6477   0.09643   0.08618  -0.0075   0.4179   1.0000
  10.500   0.6145   0.10264   0.09238  -0.0082   0.4126   1.0000
  10.750   0.6386   0.10378   0.09362  -0.0075   0.4005   1.0000
  11.000   0.6187   0.10909   0.09895  -0.0082   0.3964   1.0000
  11.250   0.5655   0.12015   0.11003  -0.0128   0.4389   1.0000
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