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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 500,000
Max Cl/Cd: 89.19 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3002-il-500000-n5.txt
Download as CSV file: xf-s3002-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3884   0.08320   0.08090  -0.0365   1.0000   0.0076
  -8.750  -0.3923   0.07919   0.07693  -0.0379   1.0000   0.0076
  -8.500  -0.4019   0.07458   0.07236  -0.0395   1.0000   0.0076
  -8.250  -0.4137   0.06979   0.06765  -0.0417   0.9985   0.0075
  -8.000  -0.4047   0.05739   0.05521  -0.0619   0.9798   0.0074
  -7.750  -0.4383   0.02057   0.01606  -0.0859   0.9456   0.0078
  -7.500  -0.4134   0.01844   0.01351  -0.0864   0.9363   0.0080
  -7.000  -0.3617   0.01601   0.01065  -0.0867   0.9182   0.0085
  -6.750  -0.3352   0.01537   0.00990  -0.0866   0.9098   0.0088
  -6.500  -0.3087   0.01489   0.00931  -0.0865   0.9008   0.0092
  -6.250  -0.2822   0.01435   0.00863  -0.0863   0.8927   0.0098
  -6.000  -0.2559   0.01366   0.00777  -0.0860   0.8844   0.0104
  -5.750  -0.2294   0.01300   0.00696  -0.0858   0.8766   0.0108
  -5.500  -0.2029   0.01242   0.00631  -0.0856   0.8688   0.0114
  -5.250  -0.1758   0.01205   0.00588  -0.0855   0.8615   0.0120
  -5.000  -0.1487   0.01165   0.00540  -0.0854   0.8537   0.0128
  -4.750  -0.1213   0.01126   0.00491  -0.0852   0.8467   0.0137
  -4.500  -0.0940   0.01088   0.00448  -0.0851   0.8390   0.0148
  -4.250  -0.0664   0.01065   0.00422  -0.0850   0.8317   0.0163
  -4.000  -0.0387   0.01042   0.00390  -0.0849   0.8236   0.0178
  -3.750  -0.0111   0.01006   0.00351  -0.0849   0.8159   0.0194
  -3.500   0.0167   0.00983   0.00322  -0.0848   0.8072   0.0212
  -3.250   0.0445   0.00960   0.00294  -0.0847   0.7990   0.0234
  -3.000   0.0724   0.00939   0.00270  -0.0846   0.7900   0.0261
  -2.750   0.1004   0.00922   0.00247  -0.0846   0.7807   0.0290
  -2.500   0.1283   0.00904   0.00226  -0.0845   0.7712   0.0332
  -2.250   0.1564   0.00886   0.00208  -0.0845   0.7610   0.0418
  -2.000   0.1845   0.00862   0.00192  -0.0845   0.7512   0.0708
  -1.750   0.2124   0.00840   0.00179  -0.0845   0.7410   0.1128
  -1.500   0.2405   0.00817   0.00169  -0.0846   0.7300   0.1661
  -1.250   0.2684   0.00784   0.00160  -0.0848   0.7188   0.2524
  -1.000   0.2962   0.00739   0.00151  -0.0851   0.7070   0.3897
  -0.750   0.3237   0.00692   0.00148  -0.0853   0.6945   0.5468
  -0.500   0.3502   0.00671   0.00159  -0.0849   0.6808   0.6682
  -0.250   0.3775   0.00675   0.00164  -0.0846   0.6660   0.7089
   0.000   0.4050   0.00682   0.00166  -0.0843   0.6503   0.7258
   0.250   0.4325   0.00691   0.00168  -0.0841   0.6333   0.7391
   0.500   0.4597   0.00702   0.00172  -0.0837   0.6143   0.7557
   0.750   0.4865   0.00713   0.00178  -0.0833   0.5939   0.7713
   1.000   0.5132   0.00728   0.00183  -0.0830   0.5721   0.7831
   1.250   0.5401   0.00743   0.00189  -0.0827   0.5485   0.7921
   1.500   0.5668   0.00759   0.00195  -0.0824   0.5250   0.7977
   1.750   0.5936   0.00776   0.00202  -0.0821   0.5011   0.8027
   2.000   0.6205   0.00796   0.00210  -0.0819   0.4770   0.8076
   2.250   0.6471   0.00815   0.00220  -0.0816   0.4533   0.8119
   2.500   0.6736   0.00835   0.00231  -0.0814   0.4299   0.8162
   2.750   0.7001   0.00856   0.00243  -0.0811   0.4073   0.8209
   3.000   0.7267   0.00879   0.00256  -0.0809   0.3854   0.8256
   3.250   0.7528   0.00900   0.00271  -0.0806   0.3638   0.8301
   3.750   0.8054   0.00945   0.00301  -0.0801   0.3258   0.8406
   4.000   0.8314   0.00966   0.00319  -0.0798   0.3081   0.8461
   4.250   0.8573   0.00990   0.00337  -0.0794   0.2904   0.8525
   4.500   0.8830   0.01013   0.00356  -0.0791   0.2735   0.8591
   4.750   0.9084   0.01036   0.00375  -0.0787   0.2573   0.8672
   5.000   0.9333   0.01060   0.00397  -0.0782   0.2413   0.8766
   5.250   0.9575   0.01085   0.00419  -0.0775   0.2247   0.8895
   5.500   0.9803   0.01107   0.00441  -0.0765   0.2093   0.9115
   5.750   1.0069   0.01129   0.00463  -0.0764   0.1941   1.0000
   6.000   1.0326   0.01164   0.00491  -0.0762   0.1788   1.0000
   6.250   1.0580   0.01200   0.00521  -0.0760   0.1643   1.0000
   6.500   1.0832   0.01237   0.00553  -0.0757   0.1512   1.0000
   6.750   1.1082   0.01274   0.00586  -0.0754   0.1391   1.0000
   7.000   1.1330   0.01312   0.00620  -0.0750   0.1272   1.0000
   7.250   1.1576   0.01351   0.00655  -0.0747   0.1173   1.0000
   7.500   1.1818   0.01392   0.00694  -0.0742   0.1081   1.0000
   8.000   1.2294   0.01478   0.00775  -0.0733   0.0899   1.0000
   8.250   1.2527   0.01523   0.00820  -0.0727   0.0826   1.0000
   8.500   1.2754   0.01572   0.00867  -0.0721   0.0751   1.0000
   8.750   1.2982   0.01618   0.00914  -0.0715   0.0690   1.0000
   9.000   1.3198   0.01673   0.00967  -0.0707   0.0627   1.0000
   9.250   1.3421   0.01720   0.01018  -0.0700   0.0583   1.0000
   9.500   1.3627   0.01778   0.01075  -0.0691   0.0531   1.0000
   9.750   1.3838   0.01830   0.01131  -0.0683   0.0497   1.0000
  10.000   1.4039   0.01886   0.01190  -0.0673   0.0463   1.0000
  10.250   1.4224   0.01954   0.01260  -0.0661   0.0429   1.0000
  10.500   1.4418   0.02008   0.01321  -0.0650   0.0408   1.0000
  10.750   1.4597   0.02070   0.01388  -0.0638   0.0385   1.0000
  11.000   1.4747   0.02141   0.01462  -0.0621   0.0363   1.0000
  11.250   1.4880   0.02213   0.01539  -0.0601   0.0345   1.0000
  11.500   1.5018   0.02279   0.01613  -0.0583   0.0331   1.0000
  11.750   1.5143   0.02355   0.01697  -0.0564   0.0317   1.0000
  12.000   1.5254   0.02442   0.01789  -0.0545   0.0303   1.0000
  12.250   1.5344   0.02546   0.01898  -0.0524   0.0288   1.0000
  12.500   1.5440   0.02649   0.02010  -0.0506   0.0277   1.0000
  12.750   1.5544   0.02751   0.02122  -0.0490   0.0268   1.0000
  13.000   1.5635   0.02867   0.02248  -0.0474   0.0258   1.0000
  13.250   1.5714   0.02998   0.02388  -0.0459   0.0248   1.0000
  13.500   1.5778   0.03146   0.02544  -0.0445   0.0239   1.0000
  13.750   1.5819   0.03322   0.02726  -0.0431   0.0230   1.0000
  14.000   1.5863   0.03502   0.02916  -0.0419   0.0222   1.0000
  14.250   1.5924   0.03674   0.03100  -0.0410   0.0214   1.0000
  14.500   1.5971   0.03867   0.03305  -0.0402   0.0206   1.0000
  14.750   1.6009   0.04077   0.03524  -0.0395   0.0196   1.0000
  15.000   1.6022   0.04323   0.03778  -0.0391   0.0188   1.0000
  15.250   1.6003   0.04617   0.04081  -0.0389   0.0180   1.0000
  15.500   1.6002   0.04902   0.04378  -0.0389   0.0174   1.0000
  15.750   1.6001   0.05200   0.04690  -0.0392   0.0167   1.0000
  16.000   1.5978   0.05542   0.05044  -0.0397   0.0161   1.0000
  16.250   1.5934   0.05927   0.05441  -0.0406   0.0155   1.0000
  16.500   1.5875   0.06353   0.05878  -0.0419   0.0149   1.0000
  16.750   1.5790   0.06841   0.06379  -0.0436   0.0145   1.0000
  17.000   1.5683   0.07386   0.06938  -0.0458   0.0143   1.0000
  17.250   1.5563   0.07975   0.07540  -0.0483   0.0140   1.0000
  17.500   1.5447   0.08577   0.08158  -0.0511   0.0137   1.0000
  17.750   1.5313   0.09228   0.08824  -0.0542   0.0135   1.0000
  18.000   1.5165   0.09922   0.09534  -0.0577   0.0134   1.0000
  18.250   1.5007   0.10651   0.10278  -0.0614   0.0132   1.0000
  18.500   1.4845   0.11402   0.11044  -0.0654   0.0130   1.0000
  18.750   1.4680   0.12171   0.11827  -0.0697   0.0128   1.0000
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