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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 100,000
Max Cl/Cd: 55.06 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4180-il-100000.txt
Download as CSV file: xf-s4180-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4180-098-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2734   0.09322   0.08862  -0.0278   1.0000   0.0901
  -7.500  -0.2791   0.09162   0.08714  -0.0297   1.0000   0.0929
  -7.250  -0.2998   0.09143   0.08714  -0.0316   1.0000   0.0940
  -7.000  -0.3203   0.09107   0.08693  -0.0338   1.0000   0.0945
  -6.750  -0.3403   0.09050   0.08644  -0.0346   1.0000   0.0947
  -6.500  -0.3439   0.08680   0.08286  -0.0290   1.0000   0.0955
  -6.250  -0.3464   0.08450   0.08064  -0.0232   1.0000   0.0966
  -6.000  -0.3480   0.08263   0.07883  -0.0200   0.9993   0.0980
  -5.750  -0.3131   0.07825   0.07442  -0.0264   0.9911   0.1033
  -5.500  -0.2678   0.07125   0.06727  -0.0466   0.9780   0.1113
  -5.250  -0.2368   0.06789   0.06394  -0.0467   0.9719   0.1165
  -5.000  -0.1944   0.06223   0.05813  -0.0602   0.9602   0.1279
  -4.500  -0.1148   0.05395   0.04969  -0.0727   0.9436   0.1472
  -4.250  -0.0629   0.05082   0.04602  -0.0854   0.9316   0.1731
  -4.000  -0.0320   0.04609   0.04152  -0.0862   0.9253   0.1775
  -3.750   0.0294   0.03464   0.02867  -0.0990   0.9146   0.0972
  -3.500   0.0666   0.03098   0.02459  -0.1013   0.9041   0.0887
  -3.250   0.1104   0.02689   0.01944  -0.1039   0.8961   0.0817
  -3.000   0.1413   0.02489   0.01704  -0.1041   0.8834   0.0818
  -2.750   0.1715   0.02323   0.01518  -0.1041   0.8714   0.0842
  -2.500   0.2022   0.02213   0.01390  -0.1038   0.8602   0.0907
  -2.250   0.2314   0.02089   0.01249  -0.1032   0.8489   0.0996
  -2.000   0.2581   0.01987   0.01138  -0.1022   0.8357   0.1133
  -1.750   0.2846   0.01911   0.01061  -0.1013   0.8230   0.1424
  -1.500   0.3105   0.01844   0.01011  -0.1005   0.8111   0.1810
  -1.250   0.3369   0.01775   0.00950  -0.0994   0.8003   0.2232
  -1.000   0.3615   0.01705   0.00913  -0.0984   0.7870   0.2878
  -0.750   0.3759   0.01523   0.00908  -0.0949   0.7753   0.7169
  -0.500   0.4072   0.01475   0.00858  -0.0938   0.7641   1.0000
  -0.250   0.4344   0.01484   0.00835  -0.0930   0.7529   1.0000
   0.000   0.4609   0.01503   0.00831  -0.0924   0.7399   1.0000
   0.250   0.4876   0.01522   0.00829  -0.0919   0.7277   1.0000
   0.500   0.5146   0.01537   0.00822  -0.0912   0.7169   1.0000
   0.750   0.5418   0.01552   0.00818  -0.0906   0.7060   1.0000
   1.000   0.5684   0.01577   0.00829  -0.0902   0.6937   1.0000
   1.250   0.5953   0.01599   0.00838  -0.0897   0.6827   1.0000
   1.500   0.6229   0.01614   0.00834  -0.0891   0.6734   1.0000
   1.750   0.6493   0.01644   0.00857  -0.0888   0.6613   1.0000
   2.000   0.6761   0.01673   0.00876  -0.0884   0.6506   1.0000
   2.250   0.7038   0.01690   0.00877  -0.0878   0.6418   1.0000
   2.500   0.7301   0.01726   0.00910  -0.0875   0.6301   1.0000
   2.750   0.7567   0.01758   0.00936  -0.0872   0.6199   1.0000
   3.000   0.7844   0.01779   0.00944  -0.0867   0.6109   1.0000
   3.250   0.8103   0.01819   0.00985  -0.0864   0.5996   1.0000
   3.500   0.8370   0.01851   0.01012  -0.0860   0.5898   1.0000
   3.750   0.8643   0.01876   0.01029  -0.0855   0.5804   1.0000
   4.000   0.8900   0.01916   0.01073  -0.0851   0.5692   1.0000
   4.250   0.9167   0.01946   0.01098  -0.0847   0.5596   1.0000
   4.500   0.9435   0.01972   0.01119  -0.0842   0.5494   1.0000
   4.750   0.9689   0.02012   0.01164  -0.0837   0.5379   1.0000
   5.000   0.9952   0.02042   0.01191  -0.0832   0.5276   1.0000
   5.250   1.0222   0.02063   0.01205  -0.0827   0.5173   1.0000
   5.500   1.0470   0.02101   0.01252  -0.0821   0.5051   1.0000
   5.750   1.0724   0.02133   0.01286  -0.0816   0.4935   1.0000
   6.000   1.0989   0.02156   0.01304  -0.0810   0.4824   1.0000
   6.250   1.1249   0.02177   0.01322  -0.0804   0.4705   1.0000
   6.500   1.1493   0.02208   0.01362  -0.0797   0.4571   1.0000
   6.750   1.1737   0.02236   0.01394  -0.0790   0.4435   1.0000
   7.000   1.1982   0.02261   0.01422  -0.0782   0.4296   1.0000
   7.250   1.2223   0.02284   0.01449  -0.0775   0.4151   1.0000
   7.500   1.2460   0.02307   0.01474  -0.0766   0.3999   1.0000
   7.750   1.2690   0.02332   0.01501  -0.0757   0.3839   1.0000
   8.000   1.2915   0.02357   0.01527  -0.0747   0.3668   1.0000
   8.250   1.3133   0.02386   0.01557  -0.0737   0.3492   1.0000
   8.500   1.3340   0.02423   0.01590  -0.0725   0.3306   1.0000
   8.750   1.3519   0.02476   0.01653  -0.0712   0.3093   1.0000
   9.000   1.3699   0.02535   0.01707  -0.0698   0.2885   1.0000
   9.250   1.3856   0.02618   0.01787  -0.0683   0.2667   1.0000
   9.500   1.4001   0.02714   0.01877  -0.0667   0.2459   1.0000
   9.750   1.4143   0.02830   0.01976  -0.0651   0.2274   1.0000
  10.000   1.4266   0.02959   0.02105  -0.0634   0.2098   1.0000
  10.250   1.4390   0.03096   0.02239  -0.0617   0.1948   1.0000
  10.500   1.4522   0.03242   0.02378  -0.0602   0.1821   1.0000
  10.750   1.4674   0.03392   0.02515  -0.0590   0.1708   1.0000
  11.000   1.4769   0.03542   0.02682  -0.0571   0.1611   1.0000
  11.250   1.4911   0.03709   0.02849  -0.0559   0.1528   1.0000
  11.500   1.5058   0.03864   0.03006  -0.0547   0.1452   1.0000
  11.750   1.5182   0.04052   0.03206  -0.0533   0.1388   1.0000
  12.000   1.5289   0.04213   0.03375  -0.0518   0.1328   1.0000
  12.250   1.5482   0.04420   0.03583  -0.0513   0.1272   1.0000
  12.500   1.5496   0.04619   0.03811  -0.0490   0.1232   1.0000
  12.750   1.5622   0.04798   0.03995  -0.0479   0.1186   1.0000
  13.000   1.5778   0.05046   0.04249  -0.0474   0.1144   1.0000
  13.250   1.5711   0.05294   0.04530  -0.0450   0.1119   1.0000
  13.500   1.5679   0.05560   0.04822  -0.0433   0.1093   1.0000
  13.750   1.5693   0.05814   0.05093  -0.0422   0.1066   1.0000
  14.000   1.5948   0.06086   0.05355  -0.0423   0.1025   1.0000
  14.250   1.5747   0.06438   0.05743  -0.0406   0.1016   1.0000
  14.500   1.5533   0.06858   0.06197  -0.0398   0.1007   1.0000
  14.750   1.5299   0.07348   0.06719  -0.0399   0.0999   1.0000
  15.000   1.5030   0.07925   0.07327  -0.0409   0.0994   1.0000
  15.250   1.4706   0.08625   0.08057  -0.0431   0.0992   1.0000
  15.500   1.4300   0.09508   0.08969  -0.0469   0.0996   1.0000
  15.750   1.3790   0.10671   0.10159  -0.0532   0.1006   1.0000
  16.000   1.3183   0.12198   0.11706  -0.0623   0.1021   1.0000
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