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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 500,000
Max Cl/Cd: 99.78 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3002-il-500000.txt
Download as CSV file: xf-s3002-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3646   0.08641   0.08415  -0.0361   1.0000   0.0192
  -8.500  -0.3634   0.08354   0.08132  -0.0367   1.0000   0.0196
  -8.250  -0.3649   0.08044   0.07826  -0.0374   1.0000   0.0198
  -8.000  -0.3700   0.07747   0.07534  -0.0376   1.0000   0.0200
  -7.750  -0.3834   0.07516   0.07310  -0.0361   1.0000   0.0202
  -7.500  -0.3885   0.07142   0.06941  -0.0390   0.9967   0.0204
  -7.250  -0.3616   0.06198   0.05993  -0.0567   0.9885   0.0210
  -7.000  -0.3317   0.04661   0.04397  -0.0773   0.9787   0.0228
  -6.750  -0.3112   0.03851   0.03555  -0.0843   0.9736   0.0234
  -6.500  -0.2841   0.03601   0.03301  -0.0871   0.9690   0.0239
  -6.250  -0.2579   0.03349   0.03035  -0.0892   0.9620   0.0247
  -6.000  -0.2374   0.02177   0.01726  -0.0911   0.9516   0.0178
  -5.750  -0.2107   0.01901   0.01409  -0.0916   0.9446   0.0177
  -5.500  -0.1845   0.01728   0.01200  -0.0913   0.9366   0.0180
  -5.250  -0.1586   0.01554   0.01000  -0.0912   0.9293   0.0190
  -5.000  -0.1327   0.01464   0.00903  -0.0908   0.9212   0.0198
  -4.750  -0.1063   0.01368   0.00794  -0.0904   0.9138   0.0204
  -4.500  -0.0800   0.01288   0.00701  -0.0899   0.9056   0.0214
  -4.250  -0.0533   0.01227   0.00628  -0.0894   0.8981   0.0225
  -4.000  -0.0275   0.01134   0.00528  -0.0889   0.8897   0.0239
  -3.750  -0.0008   0.01094   0.00485  -0.0886   0.8820   0.0262
  -3.500   0.0263   0.01063   0.00449  -0.0883   0.8734   0.0283
  -3.250   0.0530   0.00995   0.00376  -0.0880   0.8658   0.0311
  -3.000   0.0804   0.00967   0.00345  -0.0878   0.8570   0.0344
  -2.750   0.1079   0.00929   0.00302  -0.0876   0.8492   0.0392
  -2.500   0.1357   0.00904   0.00274  -0.0874   0.8401   0.0453
  -2.250   0.1635   0.00862   0.00243  -0.0873   0.8322   0.0789
  -2.000   0.1909   0.00796   0.00223  -0.0876   0.8232   0.2095
  -1.750   0.2182   0.00729   0.00209  -0.0879   0.8151   0.3829
  -1.500   0.2449   0.00663   0.00204  -0.0880   0.8062   0.5813
  -1.250   0.2714   0.00647   0.00214  -0.0874   0.7974   0.6845
  -1.000   0.2984   0.00651   0.00218  -0.0868   0.7885   0.7272
  -0.750   0.3256   0.00655   0.00223  -0.0863   0.7784   0.7537
  -0.500   0.3525   0.00661   0.00225  -0.0858   0.7688   0.7739
  -0.250   0.3796   0.00664   0.00225  -0.0853   0.7583   0.7877
   0.000   0.4070   0.00667   0.00224  -0.0849   0.7469   0.7984
   0.250   0.4344   0.00671   0.00223  -0.0846   0.7353   0.8089
   0.500   0.4608   0.00674   0.00223  -0.0839   0.7231   0.8212
   0.750   0.4868   0.00678   0.00224  -0.0832   0.7099   0.8342
   1.000   0.5130   0.00681   0.00224  -0.0826   0.6955   0.8451
   1.250   0.5399   0.00687   0.00224  -0.0822   0.6797   0.8546
   1.500   0.5662   0.00690   0.00224  -0.0817   0.6628   0.8614
   1.750   0.5934   0.00697   0.00225  -0.0814   0.6444   0.8681
   2.000   0.6197   0.00704   0.00226  -0.0809   0.6243   0.8739
   2.250   0.6460   0.00715   0.00229  -0.0805   0.6032   0.8804
   2.500   0.6723   0.00726   0.00234  -0.0801   0.5797   0.8868
   2.750   0.6978   0.00740   0.00240  -0.0796   0.5554   0.8939
   3.000   0.7232   0.00756   0.00247  -0.0790   0.5293   0.9017
   3.250   0.7480   0.00772   0.00256  -0.0784   0.5026   0.9112
   3.500   0.7718   0.00789   0.00266  -0.0775   0.4765   0.9235
   4.000   0.8262   0.00828   0.00289  -0.0774   0.4233   1.0000
   4.250   0.8540   0.00857   0.00308  -0.0776   0.3988   1.0000
   4.750   0.9085   0.00919   0.00348  -0.0778   0.3529   1.0000
   5.000   0.9351   0.00952   0.00372  -0.0778   0.3314   1.0000
   5.250   0.9615   0.00984   0.00395  -0.0777   0.3108   1.0000
   5.500   0.9877   0.01017   0.00419  -0.0776   0.2906   1.0000
   5.750   1.0135   0.01052   0.00445  -0.0774   0.2710   1.0000
   6.000   1.0390   0.01088   0.00474  -0.0771   0.2518   1.0000
   6.250   1.0645   0.01123   0.00502  -0.0769   0.2332   1.0000
   6.500   1.0895   0.01162   0.00533  -0.0766   0.2153   1.0000
   6.750   1.1143   0.01202   0.00567  -0.0762   0.1986   1.0000
   7.000   1.1387   0.01245   0.00602  -0.0758   0.1822   1.0000
   7.250   1.1629   0.01288   0.00639  -0.0754   0.1673   1.0000
   7.500   1.1869   0.01332   0.00679  -0.0749   0.1534   1.0000
   7.750   1.2106   0.01378   0.00720  -0.0744   0.1398   1.0000
   8.000   1.2339   0.01425   0.00763  -0.0738   0.1270   1.0000
   8.250   1.2570   0.01473   0.00809  -0.0733   0.1155   1.0000
   8.500   1.2796   0.01524   0.00858  -0.0726   0.1048   1.0000
   8.750   1.3015   0.01580   0.00911  -0.0719   0.0947   1.0000
   9.000   1.3223   0.01644   0.00971  -0.0710   0.0853   1.0000
   9.250   1.3439   0.01698   0.01025  -0.0702   0.0779   1.0000
   9.500   1.3641   0.01762   0.01091  -0.0692   0.0712   1.0000
   9.750   1.3835   0.01828   0.01156  -0.0681   0.0652   1.0000
  10.000   1.4021   0.01898   0.01231  -0.0669   0.0606   1.0000
  10.250   1.4210   0.01961   0.01296  -0.0657   0.0565   1.0000
  10.500   1.4339   0.02065   0.01401  -0.0638   0.0522   1.0000
  10.750   1.4521   0.02119   0.01464  -0.0625   0.0500   1.0000
  11.000   1.4667   0.02185   0.01536  -0.0607   0.0475   1.0000
  11.250   1.4769   0.02274   0.01628  -0.0583   0.0450   1.0000
  11.500   1.4818   0.02399   0.01759  -0.0554   0.0428   1.0000
  11.750   1.4953   0.02473   0.01845  -0.0538   0.0414   1.0000
  12.000   1.5066   0.02564   0.01944  -0.0520   0.0397   1.0000
  12.250   1.5167   0.02665   0.02051  -0.0502   0.0380   1.0000
  12.500   1.5217   0.02809   0.02199  -0.0481   0.0364   1.0000
  12.750   1.5189   0.03022   0.02421  -0.0456   0.0349   1.0000
  13.000   1.5298   0.03136   0.02547  -0.0444   0.0340   1.0000
  13.250   1.5382   0.03275   0.02697  -0.0432   0.0328   1.0000
  13.500   1.5453   0.03430   0.02861  -0.0420   0.0316   1.0000
  13.750   1.5507   0.03605   0.03045  -0.0410   0.0305   1.0000
  14.000   1.5518   0.03829   0.03277  -0.0400   0.0295   1.0000
  14.250   1.5446   0.04152   0.03608  -0.0390   0.0284   1.0000
  14.500   1.5453   0.04409   0.03878  -0.0384   0.0277   1.0000
  14.750   1.5506   0.04625   0.04108  -0.0383   0.0268   1.0000
  15.000   1.5537   0.04874   0.04368  -0.0382   0.0259   1.0000
  15.250   1.5552   0.05151   0.04656  -0.0385   0.0250   1.0000
  15.500   1.5545   0.05465   0.04980  -0.0389   0.0242   1.0000
  15.750   1.5495   0.05853   0.05376  -0.0398   0.0235   1.0000
  16.000   1.5385   0.06340   0.05872  -0.0410   0.0228   1.0000
  16.250   1.5286   0.06835   0.06380  -0.0425   0.0222   1.0000
  16.500   1.5262   0.07250   0.06811  -0.0441   0.0218   1.0000
  16.750   1.5211   0.07716   0.07294  -0.0460   0.0213   1.0000
  17.000   1.5146   0.08222   0.07813  -0.0483   0.0207   1.0000
  17.250   1.5070   0.08762   0.08367  -0.0508   0.0202   1.0000
  17.500   1.4981   0.09333   0.08950  -0.0535   0.0198   1.0000
  17.750   1.4886   0.09931   0.09559  -0.0565   0.0194   1.0000
  18.000   1.4781   0.10560   0.10199  -0.0598   0.0190   1.0000
  18.250   1.4666   0.11210   0.10859  -0.0633   0.0186   1.0000
  18.500   1.4541   0.11882   0.11540  -0.0669   0.0183   1.0000
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