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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 200,000
Max Cl/Cd: 76.57 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3002-il-200000.txt
Download as CSV file: xf-s3002-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3684   0.09270   0.08920  -0.0401   1.0000   0.0438
  -8.500  -0.3775   0.08914   0.08573  -0.0431   1.0000   0.0440
  -8.250  -0.3887   0.08585   0.08253  -0.0448   1.0000   0.0440
  -8.000  -0.3760   0.08205   0.07875  -0.0400   1.0000   0.0452
  -7.750  -0.3733   0.08011   0.07686  -0.0378   1.0000   0.0461
  -7.500  -0.3844   0.07825   0.07509  -0.0357   1.0000   0.0466
  -7.250  -0.4026   0.07661   0.07355  -0.0332   1.0000   0.0468
  -7.000  -0.4207   0.07465   0.07167  -0.0318   1.0000   0.0471
  -6.750  -0.4353   0.07216   0.06922  -0.0316   1.0000   0.0474
  -6.500  -0.4224   0.06766   0.06467  -0.0372   0.9967   0.0493
  -6.000  -0.3623   0.05256   0.04905  -0.0595   0.9843   0.0567
  -5.750  -0.3367   0.04975   0.04621  -0.0620   0.9785   0.0596
  -5.500  -0.3007   0.04369   0.03958  -0.0700   0.9730   0.0684
  -5.250  -0.2728   0.04165   0.03764  -0.0717   0.9683   0.0736
  -5.000  -0.2401   0.03759   0.03317  -0.0759   0.9623   0.0831
  -4.750  -0.1933   0.02748   0.02139  -0.0792   0.9592   0.0446
  -4.500  -0.1584   0.02378   0.01744  -0.0812   0.9557   0.0409
  -4.250  -0.1255   0.02128   0.01451  -0.0820   0.9498   0.0399
  -4.000  -0.0856   0.01994   0.01284  -0.0841   0.9463   0.0429
  -3.750  -0.0432   0.01851   0.01113  -0.0865   0.9440   0.0440
  -3.500  -0.0106   0.01677   0.00941  -0.0874   0.9387   0.0470
  -3.250   0.0246   0.01602   0.00864  -0.0887   0.9331   0.0524
  -3.000   0.0631   0.01485   0.00749  -0.0906   0.9294   0.0580
  -2.750   0.0950   0.01428   0.00691  -0.0912   0.9224   0.0670
  -2.500   0.1288   0.01340   0.00614  -0.0923   0.9161   0.0873
  -2.250   0.1609   0.01145   0.00549  -0.0941   0.9107   0.3853
  -2.000   0.1816   0.01069   0.00575  -0.0920   0.9015   0.6663
  -1.750   0.2091   0.01071   0.00580  -0.0909   0.8945   0.7398
  -1.500   0.2309   0.01079   0.00590  -0.0884   0.8849   0.7887
  -1.250   0.2521   0.01081   0.00592  -0.0859   0.8760   0.8238
  -1.000   0.2740   0.01071   0.00579  -0.0835   0.8674   0.8459
  -0.750   0.2946   0.01065   0.00569  -0.0812   0.8572   0.8660
  -0.500   0.3180   0.01051   0.00547  -0.0793   0.8493   0.8840
  -0.250   0.3366   0.01038   0.00533  -0.0767   0.8382   0.9019
   0.000   0.3545   0.01021   0.00514  -0.0736   0.8280   0.9253
   0.250   0.3801   0.00997   0.00485  -0.0721   0.8192   0.9503
   0.500   0.4168   0.00984   0.00467  -0.0734   0.8077   0.9697
   0.750   0.4579   0.00972   0.00448  -0.0759   0.7966   0.9830
   1.000   0.4981   0.00962   0.00428  -0.0783   0.7851   0.9959
   1.250   0.5236   0.00960   0.00418  -0.0779   0.7726   1.0000
   1.500   0.5477   0.00962   0.00413  -0.0773   0.7583   1.0000
   1.750   0.5745   0.00964   0.00409  -0.0772   0.7435   1.0000
   2.000   0.6025   0.00967   0.00404  -0.0772   0.7280   1.0000
   2.250   0.6309   0.00971   0.00400  -0.0773   0.7115   1.0000
   2.500   0.6592   0.00978   0.00401  -0.0774   0.6931   1.0000
   2.750   0.6873   0.00986   0.00402  -0.0774   0.6728   1.0000
   3.000   0.7153   0.00997   0.00403  -0.0774   0.6519   1.0000
   3.250   0.7429   0.01012   0.00408  -0.0773   0.6287   1.0000
   3.500   0.7700   0.01030   0.00415  -0.0770   0.6044   1.0000
   3.750   0.7966   0.01052   0.00426  -0.0768   0.5775   1.0000
   4.000   0.8227   0.01078   0.00440  -0.0764   0.5497   1.0000
   4.250   0.8484   0.01108   0.00459  -0.0760   0.5213   1.0000
   4.500   0.8737   0.01143   0.00479  -0.0756   0.4931   1.0000
   4.750   0.8986   0.01182   0.00503  -0.0751   0.4654   1.0000
   5.000   0.9234   0.01221   0.00531  -0.0747   0.4382   1.0000
   5.250   0.9479   0.01262   0.00564  -0.0742   0.4123   1.0000
   5.500   0.9721   0.01308   0.00597  -0.0736   0.3880   1.0000
   5.750   0.9962   0.01352   0.00633  -0.0731   0.3638   1.0000
   6.000   1.0199   0.01400   0.00673  -0.0726   0.3413   1.0000
   6.250   1.0435   0.01447   0.00714  -0.0720   0.3187   1.0000
   6.500   1.0665   0.01501   0.00757  -0.0714   0.2978   1.0000
   6.750   1.0898   0.01549   0.00804  -0.0708   0.2763   1.0000
   7.000   1.1122   0.01605   0.00852  -0.0701   0.2564   1.0000
   7.250   1.1342   0.01663   0.00904  -0.0693   0.2372   1.0000
   7.500   1.1563   0.01720   0.00959  -0.0686   0.2184   1.0000
   7.750   1.1777   0.01783   0.01019  -0.0678   0.2008   1.0000
   8.000   1.1984   0.01851   0.01082  -0.0669   0.1844   1.0000
   8.250   1.2183   0.01923   0.01150  -0.0659   0.1690   1.0000
   8.500   1.2378   0.02000   0.01223  -0.0649   0.1546   1.0000
   8.750   1.2568   0.02080   0.01303  -0.0638   0.1415   1.0000
   9.000   1.2750   0.02163   0.01388  -0.0626   0.1295   1.0000
   9.250   1.2921   0.02256   0.01480  -0.0613   0.1187   1.0000
   9.500   1.3074   0.02363   0.01581  -0.0597   0.1097   1.0000
   9.750   1.3238   0.02451   0.01677  -0.0583   0.1015   1.0000
  10.000   1.3382   0.02565   0.01794  -0.0567   0.0946   1.0000
  10.250   1.3511   0.02662   0.01894  -0.0548   0.0886   1.0000
  10.500   1.3634   0.02795   0.02030  -0.0530   0.0836   1.0000
  10.750   1.3759   0.02897   0.02143  -0.0511   0.0790   1.0000
  11.000   1.3869   0.03038   0.02281  -0.0494   0.0748   1.0000
  11.250   1.3992   0.03174   0.02432  -0.0478   0.0714   1.0000
  11.500   1.4102   0.03298   0.02569  -0.0461   0.0681   1.0000
  11.750   1.4203   0.03433   0.02708  -0.0445   0.0652   1.0000
  12.000   1.4337   0.03637   0.02913  -0.0434   0.0620   1.0000
  12.250   1.4409   0.03783   0.03082  -0.0416   0.0599   1.0000
  12.500   1.4484   0.03947   0.03264  -0.0401   0.0576   1.0000
  12.750   1.4559   0.04111   0.03437  -0.0387   0.0554   1.0000
  13.000   1.4662   0.04320   0.03645  -0.0378   0.0531   1.0000
  13.250   1.4706   0.04573   0.03920  -0.0365   0.0514   1.0000
  13.500   1.4713   0.04800   0.04172  -0.0351   0.0500   1.0000
  13.750   1.4716   0.05049   0.04442  -0.0341   0.0486   1.0000
  14.000   1.4711   0.05306   0.04716  -0.0332   0.0471   1.0000
  14.250   1.4720   0.05554   0.04975  -0.0327   0.0457   1.0000
  14.500   1.4754   0.05816   0.05240  -0.0323   0.0442   1.0000
  14.750   1.4709   0.06270   0.05714  -0.0320   0.0429   1.0000
  15.000   1.4594   0.06666   0.06137  -0.0323   0.0424   1.0000
  15.250   1.4460   0.07120   0.06619  -0.0332   0.0419   1.0000
  15.500   1.4310   0.07632   0.07157  -0.0346   0.0414   1.0000
  15.750   1.4139   0.08207   0.07757  -0.0367   0.0409   1.0000
  16.000   1.3949   0.08854   0.08428  -0.0396   0.0405   1.0000
  16.250   1.3732   0.09592   0.09191  -0.0435   0.0403   1.0000
  16.500   1.3476   0.10459   0.10083  -0.0485   0.0402   1.0000
  16.750   1.3157   0.11523   0.11170  -0.0552   0.0405   1.0000
  17.000   1.2754   0.12868   0.12539  -0.0643   0.0413   1.0000
  17.250   1.2235   0.14633   0.14324  -0.0764   0.0424   1.0000
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