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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 100,000
Max Cl/Cd: 56.31 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3002-il-100000.txt
Download as CSV file: xf-s3002-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SELIG 3002-099-83                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3551   0.10261   0.09761  -0.0312   1.0000   0.0908
  -8.750  -0.3698   0.10080   0.09592  -0.0355   1.0000   0.0932
  -8.500  -0.3885   0.09902   0.09428  -0.0390   1.0000   0.0937
  -8.250  -0.3544   0.09321   0.08841  -0.0336   1.0000   0.0978
  -8.000  -0.3506   0.09053   0.08579  -0.0330   1.0000   0.1014
  -7.750  -0.3575   0.08816   0.08352  -0.0335   1.0000   0.1050
  -7.500  -0.3815   0.08666   0.08219  -0.0342   1.0000   0.1071
  -7.250  -0.4098   0.08443   0.08009  -0.0390   1.0000   0.1081
  -7.000  -0.4373   0.08263   0.07822  -0.0422   1.0000   0.1086
  -6.750  -0.4056   0.07854   0.07435  -0.0312   1.0000   0.1122
  -6.500  -0.4102   0.07651   0.07239  -0.0290   1.0000   0.1151
  -6.250  -0.4199   0.07407   0.06999  -0.0292   1.0000   0.1185
  -6.000  -0.4402   0.07011   0.06580  -0.0376   1.0000   0.1243
  -5.750  -0.4334   0.06731   0.06318  -0.0327   1.0000   0.1265
  -5.500  -0.4292   0.06516   0.06108  -0.0304   1.0000   0.1306
  -5.250  -0.4262   0.06102   0.05674  -0.0351   1.0000   0.1408
  -5.000  -0.4187   0.05876   0.05457  -0.0325   1.0000   0.1450
  -4.750  -0.4079   0.05526   0.05091  -0.0352   1.0000   0.1573
  -4.500  -0.3943   0.05242   0.04792  -0.0368   1.0000   0.1717
  -4.250  -0.3814   0.05014   0.04567  -0.0357   1.0000   0.1811
  -4.000  -0.3639   0.04733   0.04277  -0.0370   0.9992   0.2043
  -3.750  -0.2773   0.03309   0.02601  -0.0496   0.9984   0.0786
  -3.500  -0.2342   0.02919   0.02166  -0.0530   0.9946   0.0728
  -3.250  -0.1911   0.02654   0.01838  -0.0556   0.9896   0.0709
  -3.000  -0.1472   0.02511   0.01662  -0.0586   0.9843   0.0760
  -2.750  -0.1076   0.02372   0.01489  -0.0605   0.9777   0.0786
  -2.500  -0.0647   0.02246   0.01365  -0.0634   0.9722   0.0875
  -2.250  -0.0284   0.02143   0.01262  -0.0649   0.9645   0.0971
  -2.000   0.0155   0.02057   0.01191  -0.0680   0.9583   0.1206
  -1.750   0.0473   0.01766   0.01122  -0.0695   0.9519   0.5242
  -1.500   0.0664   0.01777   0.01200  -0.0650   0.9432   0.8045
  -1.250   0.0770   0.01772   0.01201  -0.0597   0.9316   0.8812
  -1.000   0.1334   0.01743   0.01164  -0.0632   0.9256   1.0000
  -0.750   0.1733   0.01749   0.01146  -0.0660   0.9151   1.0000
  -0.500   0.2120   0.01756   0.01133  -0.0684   0.9045   1.0000
  -0.250   0.2652   0.01749   0.01107  -0.0731   0.8976   1.0000
   0.000   0.3010   0.01750   0.01095  -0.0748   0.8858   1.0000
   0.250   0.3437   0.01742   0.01075  -0.0774   0.8764   1.0000
   0.500   0.3873   0.01723   0.01045  -0.0799   0.8675   1.0000
   0.750   0.4210   0.01718   0.01033  -0.0808   0.8552   1.0000
   1.000   0.4575   0.01703   0.01011  -0.0819   0.8443   1.0000
   1.250   0.4974   0.01673   0.00974  -0.0833   0.8349   1.0000
   1.500   0.5276   0.01663   0.00960  -0.0832   0.8212   1.0000
   1.750   0.5582   0.01651   0.00943  -0.0831   0.8074   1.0000
   2.000   0.5886   0.01636   0.00924  -0.0829   0.7932   1.0000
   2.250   0.6187   0.01619   0.00904  -0.0825   0.7784   1.0000
   2.500   0.6482   0.01602   0.00883  -0.0820   0.7628   1.0000
   2.750   0.6773   0.01585   0.00862  -0.0814   0.7463   1.0000
   3.000   0.7063   0.01568   0.00839  -0.0808   0.7289   1.0000
   3.250   0.7353   0.01551   0.00815  -0.0801   0.7109   1.0000
   3.500   0.7612   0.01551   0.00815  -0.0792   0.6881   1.0000
   3.750   0.7890   0.01544   0.00799  -0.0784   0.6667   1.0000
   4.000   0.8150   0.01550   0.00800  -0.0776   0.6418   1.0000
   4.250   0.8418   0.01557   0.00796  -0.0768   0.6171   1.0000
   4.500   0.8675   0.01574   0.00804  -0.0759   0.5901   1.0000
   4.750   0.8925   0.01600   0.00820  -0.0750   0.5618   1.0000
   5.000   0.9172   0.01632   0.00841  -0.0742   0.5334   1.0000
   5.250   0.9415   0.01672   0.00870  -0.0733   0.5051   1.0000
   5.500   0.9656   0.01718   0.00903  -0.0725   0.4776   1.0000
   5.750   0.9894   0.01770   0.00939  -0.0716   0.4510   1.0000
   6.000   1.0124   0.01827   0.00988  -0.0707   0.4237   1.0000
   6.250   1.0352   0.01888   0.01043  -0.0699   0.3977   1.0000
   6.500   1.0580   0.01955   0.01095  -0.0691   0.3737   1.0000
   6.750   1.0799   0.02022   0.01159  -0.0681   0.3488   1.0000
   7.000   1.1018   0.02097   0.01225  -0.0673   0.3260   1.0000
   7.250   1.1230   0.02171   0.01295  -0.0663   0.3031   1.0000
   7.500   1.1442   0.02254   0.01368  -0.0654   0.2822   1.0000
   7.750   1.1643   0.02335   0.01451  -0.0643   0.2609   1.0000
   8.000   1.1845   0.02423   0.01534  -0.0633   0.2417   1.0000
   8.250   1.2045   0.02523   0.01622  -0.0624   0.2236   1.0000
   8.500   1.2234   0.02623   0.01728  -0.0612   0.2060   1.0000
   8.750   1.2422   0.02731   0.01839  -0.0601   0.1897   1.0000
   9.000   1.2609   0.02849   0.01958  -0.0590   0.1751   1.0000
   9.250   1.2797   0.02977   0.02085  -0.0579   0.1620   1.0000
   9.500   1.2989   0.03113   0.02217  -0.0570   0.1502   1.0000
   9.750   1.3182   0.03250   0.02354  -0.0561   0.1397   1.0000
  10.000   1.3351   0.03407   0.02535  -0.0548   0.1304   1.0000
  10.250   1.3551   0.03579   0.02704  -0.0541   0.1224   1.0000
  10.500   1.3714   0.03739   0.02885  -0.0528   0.1154   1.0000
  10.750   1.3911   0.03950   0.03100  -0.0522   0.1093   1.0000
  11.000   1.4028   0.04129   0.03312  -0.0504   0.1038   1.0000
  11.250   1.4280   0.04380   0.03545  -0.0507   0.0984   1.0000
  11.500   1.4307   0.04601   0.03820  -0.0480   0.0953   1.0000
  11.750   1.4371   0.04823   0.04073  -0.0460   0.0915   1.0000
  12.000   1.4502   0.05023   0.04278  -0.0449   0.0877   1.0000
  12.250   1.4581   0.05383   0.04657  -0.0437   0.0852   1.0000
  12.500   1.4451   0.05668   0.04988  -0.0400   0.0839   1.0000
  12.750   1.4285   0.05976   0.05331  -0.0366   0.0828   1.0000
  13.000   1.4098   0.06328   0.05716  -0.0340   0.0818   1.0000
  13.250   1.3885   0.06735   0.06153  -0.0323   0.0811   1.0000
  13.500   1.3633   0.07224   0.06672  -0.0316   0.0808   1.0000
  13.750   1.3324   0.07829   0.07305  -0.0323   0.0810   1.0000
  14.000   1.2950   0.08598   0.08101  -0.0348   0.0818   1.0000
  14.250   1.2532   0.09551   0.09077  -0.0395   0.0831   1.0000
  14.500   1.2109   0.10677   0.10218  -0.0460   0.0845   1.0000
  14.750   1.1721   0.11924   0.11474  -0.0535   0.0856   1.0000
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