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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 200,000
Max Cl/Cd: 70.81 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3002-il-200000-n5.txt
Download as CSV file: xf-s3002-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3651   0.08756   0.08397  -0.0358   1.0000   0.0161
  -8.500  -0.3679   0.08371   0.08018  -0.0370   1.0000   0.0158
  -8.000  -0.4098   0.07096   0.06763  -0.0416   1.0000   0.0140
  -7.750  -0.4237   0.06835   0.06512  -0.0413   1.0000   0.0139
  -7.500  -0.4103   0.06044   0.05713  -0.0532   0.9913   0.0138
  -7.250  -0.3916   0.05166   0.04812  -0.0641   0.9818   0.0137
  -6.750  -0.3511   0.03644   0.03202  -0.0772   0.9641   0.0146
  -6.500  -0.3223   0.03358   0.02888  -0.0803   0.9588   0.0153
  -6.250  -0.2983   0.02880   0.02350  -0.0824   0.9505   0.0155
  -6.000  -0.2688   0.02502   0.01911  -0.0843   0.9448   0.0159
  -5.750  -0.2405   0.02236   0.01594  -0.0851   0.9381   0.0165
  -5.500  -0.2106   0.02026   0.01338  -0.0858   0.9318   0.0173
  -5.250  -0.1793   0.01872   0.01154  -0.0867   0.9269   0.0183
  -5.000  -0.1517   0.01804   0.01081  -0.0869   0.9191   0.0199
  -4.750  -0.1209   0.01707   0.00964  -0.0874   0.9136   0.0217
  -4.500  -0.0934   0.01605   0.00847  -0.0873   0.9061   0.0229
  -4.250  -0.0648   0.01523   0.00765  -0.0875   0.8995   0.0244
  -4.000  -0.0368   0.01468   0.00702  -0.0875   0.8922   0.0272
  -3.750  -0.0091   0.01403   0.00633  -0.0875   0.8847   0.0300
  -3.500   0.0188   0.01354   0.00580  -0.0874   0.8774   0.0330
  -3.250   0.0463   0.01307   0.00528  -0.0873   0.8693   0.0371
  -3.000   0.0741   0.01269   0.00484  -0.0872   0.8615   0.0417
  -2.750   0.1017   0.01232   0.00445  -0.0870   0.8531   0.0497
  -2.500   0.1293   0.01195   0.00409  -0.0869   0.8444   0.0660
  -2.250   0.1568   0.01147   0.00381  -0.0868   0.8359   0.1216
  -2.000   0.1838   0.01100   0.00361  -0.0869   0.8263   0.2033
  -1.750   0.2109   0.01039   0.00342  -0.0870   0.8176   0.3368
  -1.500   0.2337   0.00951   0.00355  -0.0861   0.8073   0.6083
  -1.250   0.2576   0.00948   0.00372  -0.0846   0.7973   0.7061
  -1.000   0.2838   0.00952   0.00370  -0.0837   0.7878   0.7395
  -0.750   0.3101   0.00956   0.00368  -0.0830   0.7767   0.7621
  -0.500   0.3366   0.00958   0.00364  -0.0824   0.7660   0.7797
  -0.250   0.3618   0.00959   0.00361  -0.0813   0.7554   0.7984
   0.000   0.3861   0.00960   0.00360  -0.0801   0.7435   0.8197
   0.250   0.4107   0.00960   0.00357  -0.0790   0.7311   0.8372
   0.500   0.4359   0.00959   0.00352  -0.0780   0.7182   0.8489
   0.750   0.4621   0.00959   0.00346  -0.0774   0.7044   0.8577
   1.000   0.4882   0.00960   0.00340  -0.0768   0.6897   0.8656
   1.250   0.5143   0.00963   0.00336  -0.0763   0.6738   0.8731
   1.500   0.5403   0.00966   0.00333  -0.0757   0.6565   0.8810
   1.750   0.5661   0.00971   0.00331  -0.0750   0.6379   0.8889
   2.000   0.5919   0.00978   0.00330  -0.0744   0.6181   0.8981
   2.250   0.6174   0.00986   0.00330  -0.0737   0.5961   0.9082
   2.750   0.6704   0.01008   0.00336  -0.0729   0.5486   0.9386
   3.000   0.7019   0.01024   0.00342  -0.0737   0.5227   0.9821
   3.250   0.7292   0.01051   0.00355  -0.0738   0.4971   1.0000
   3.500   0.7561   0.01080   0.00372  -0.0737   0.4715   1.0000
   3.750   0.7825   0.01111   0.00390  -0.0736   0.4465   1.0000
   4.000   0.8086   0.01145   0.00411  -0.0735   0.4217   1.0000
   4.250   0.8346   0.01179   0.00435  -0.0733   0.3982   1.0000
   4.500   0.8602   0.01216   0.00461  -0.0731   0.3754   1.0000
   4.750   0.8858   0.01251   0.00488  -0.0729   0.3544   1.0000
   5.000   0.9113   0.01288   0.00518  -0.0726   0.3340   1.0000
   5.250   0.9363   0.01328   0.00549  -0.0723   0.3144   1.0000
   5.500   0.9613   0.01367   0.00582  -0.0720   0.2955   1.0000
   5.750   0.9861   0.01407   0.00618  -0.0716   0.2769   1.0000
   6.000   1.0106   0.01450   0.00655  -0.0712   0.2588   1.0000
   6.250   1.0346   0.01495   0.00694  -0.0708   0.2409   1.0000
   6.500   1.0583   0.01543   0.00736  -0.0703   0.2239   1.0000
   6.750   1.0819   0.01590   0.00781  -0.0698   0.2072   1.0000
   7.000   1.1053   0.01640   0.00827  -0.0693   0.1915   1.0000
   7.250   1.1282   0.01692   0.00876  -0.0688   0.1763   1.0000
   7.500   1.1507   0.01746   0.00929  -0.0681   0.1621   1.0000
   7.750   1.1727   0.01804   0.00984  -0.0675   0.1492   1.0000
   8.000   1.1943   0.01864   0.01042  -0.0667   0.1370   1.0000
   8.250   1.2156   0.01924   0.01102  -0.0660   0.1254   1.0000
   8.500   1.2366   0.01986   0.01167  -0.0651   0.1149   1.0000
   8.750   1.2568   0.02052   0.01235  -0.0642   0.1059   1.0000
   9.000   1.2757   0.02126   0.01308  -0.0632   0.0974   1.0000
   9.250   1.2950   0.02195   0.01382  -0.0622   0.0895   1.0000
   9.500   1.3126   0.02273   0.01465  -0.0610   0.0828   1.0000
   9.750   1.3296   0.02352   0.01548  -0.0597   0.0766   1.0000
  10.000   1.3448   0.02438   0.01639  -0.0582   0.0715   1.0000
  10.250   1.3588   0.02520   0.01728  -0.0564   0.0668   1.0000
  10.500   1.3692   0.02623   0.01833  -0.0544   0.0628   1.0000
  10.750   1.3817   0.02714   0.01937  -0.0526   0.0596   1.0000
  11.000   1.3928   0.02816   0.02048  -0.0508   0.0563   1.0000
  11.250   1.4009   0.02939   0.02176  -0.0488   0.0535   1.0000
  11.500   1.4087   0.03071   0.02316  -0.0470   0.0512   1.0000
  11.750   1.4180   0.03198   0.02457  -0.0455   0.0490   1.0000
  12.000   1.4258   0.03339   0.02610  -0.0440   0.0469   1.0000
  12.250   1.4314   0.03502   0.02781  -0.0425   0.0450   1.0000
  12.500   1.4335   0.03703   0.02990  -0.0411   0.0433   1.0000
  12.750   1.4394   0.03883   0.03184  -0.0400   0.0419   1.0000
  13.000   1.4446   0.04074   0.03392  -0.0390   0.0403   1.0000
  13.250   1.4482   0.04288   0.03619  -0.0382   0.0389   1.0000
  13.500   1.4507   0.04519   0.03863  -0.0376   0.0376   1.0000
  13.750   1.4511   0.04783   0.04137  -0.0373   0.0365   1.0000
  14.000   1.4484   0.05091   0.04453  -0.0371   0.0354   1.0000
  14.250   1.4472   0.05399   0.04774  -0.0371   0.0345   1.0000
  14.500   1.4470   0.05707   0.05102  -0.0373   0.0336   1.0000
  14.750   1.4452   0.06047   0.05461  -0.0378   0.0327   1.0000
  15.000   1.4421   0.06414   0.05845  -0.0386   0.0318   1.0000
  15.250   1.4382   0.06810   0.06256  -0.0397   0.0310   1.0000
  15.500   1.4330   0.07238   0.06698  -0.0411   0.0303   1.0000
  15.750   1.4269   0.07698   0.07171  -0.0429   0.0296   1.0000
  16.000   1.4197   0.08192   0.07676  -0.0449   0.0290   1.0000
  16.250   1.4115   0.08712   0.08206  -0.0471   0.0284   1.0000
  16.500   1.4033   0.09251   0.08760  -0.0495   0.0279   1.0000
  16.750   1.3944   0.09830   0.09360  -0.0523   0.0275   1.0000
  17.000   1.3846   0.10441   0.09990  -0.0554   0.0270   1.0000
  17.250   1.3738   0.11082   0.10650  -0.0588   0.0265   1.0000
  17.500   1.3623   0.11755   0.11341  -0.0626   0.0261   1.0000
  17.750   1.3504   0.12454   0.12057  -0.0667   0.0256   1.0000
  18.000   1.3377   0.13185   0.12804  -0.0711   0.0252   1.0000
  18.250   1.3244   0.13943   0.13578  -0.0758   0.0249   1.0000
  18.500   1.3104   0.14743   0.14392  -0.0809   0.0245   1.0000
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