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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.6 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4180-il-1000000-n5.txt
Download as CSV file: xf-s4180-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3653   0.10642   0.10470  -0.0193   1.0000   0.0082
  -9.000  -0.5284   0.02710   0.02424  -0.0822   0.8426   0.0096
  -8.750  -0.5120   0.02280   0.01943  -0.0842   0.8298   0.0097
  -8.500  -0.4895   0.02077   0.01709  -0.0849   0.8176   0.0099
  -8.250  -0.4651   0.01936   0.01543  -0.0852   0.8060   0.0101
  -8.000  -0.4400   0.01806   0.01388  -0.0854   0.7949   0.0103
  -7.750  -0.4143   0.01698   0.01257  -0.0856   0.7835   0.0104
  -7.500  -0.3878   0.01607   0.01147  -0.0857   0.7721   0.0105
  -7.250  -0.3610   0.01531   0.01053  -0.0857   0.7610   0.0106
  -7.000  -0.3338   0.01468   0.00973  -0.0857   0.7497   0.0107
  -6.750  -0.3072   0.01351   0.00834  -0.0859   0.7379   0.0110
  -6.500  -0.2797   0.01285   0.00756  -0.0859   0.7265   0.0112
  -6.250  -0.2520   0.01237   0.00696  -0.0859   0.7149   0.0113
  -6.000  -0.2241   0.01197   0.00645  -0.0859   0.7032   0.0115
  -5.750  -0.1960   0.01159   0.00598  -0.0859   0.6912   0.0117
  -5.500  -0.1678   0.01123   0.00552  -0.0859   0.6798   0.0119
  -5.250  -0.1396   0.01089   0.00508  -0.0859   0.6686   0.0121
  -5.000  -0.1113   0.01058   0.00467  -0.0859   0.6566   0.0124
  -4.750  -0.0829   0.01029   0.00429  -0.0858   0.6453   0.0126
  -4.500  -0.0545   0.01001   0.00393  -0.0858   0.6346   0.0129
  -4.250  -0.0260   0.00977   0.00361  -0.0858   0.6235   0.0131
  -4.000   0.0025   0.00958   0.00334  -0.0858   0.6121   0.0135
  -3.750   0.0311   0.00942   0.00311  -0.0857   0.6021   0.0137
  -3.500   0.0597   0.00914   0.00276  -0.0858   0.5916   0.0142
  -3.250   0.0883   0.00894   0.00249  -0.0858   0.5806   0.0147
  -3.000   0.1170   0.00878   0.00229  -0.0858   0.5705   0.0152
  -2.750   0.1457   0.00866   0.00211  -0.0857   0.5606   0.0157
  -2.500   0.1744   0.00856   0.00195  -0.0857   0.5498   0.0163
  -2.250   0.2031   0.00846   0.00181  -0.0857   0.5403   0.0169
  -2.000   0.2318   0.00839   0.00168  -0.0857   0.5306   0.0175
  -1.750   0.2605   0.00829   0.00155  -0.0857   0.5208   0.0190
  -1.500   0.2892   0.00823   0.00146  -0.0857   0.5118   0.0212
  -1.250   0.3179   0.00814   0.00137  -0.0857   0.5024   0.0298
  -1.000   0.3466   0.00805   0.00131  -0.0858   0.4937   0.0467
  -0.750   0.3752   0.00802   0.00128  -0.0858   0.4850   0.0575
  -0.500   0.4040   0.00797   0.00125  -0.0858   0.4768   0.0692
  -0.250   0.4326   0.00794   0.00124  -0.0858   0.4684   0.0858
   0.000   0.4613   0.00790   0.00123  -0.0859   0.4606   0.1063
   0.250   0.4898   0.00787   0.00123  -0.0859   0.4527   0.1314
   0.500   0.5185   0.00782   0.00124  -0.0860   0.4449   0.1632
   1.000   0.5757   0.00763   0.00131  -0.0862   0.4296   0.2828
   1.250   0.6042   0.00757   0.00136  -0.0863   0.4221   0.3479
   1.500   0.6328   0.00741   0.00142  -0.0865   0.4143   0.4463
   1.750   0.6612   0.00719   0.00152  -0.0867   0.4064   0.5873
   2.000   0.6891   0.00696   0.00162  -0.0867   0.3982   0.7255
   2.250   0.7136   0.00672   0.00173  -0.0858   0.3902   0.8650
   2.500   0.7386   0.00660   0.00175  -0.0848   0.3816   1.0000
   2.750   0.7669   0.00673   0.00182  -0.0848   0.3731   1.0000
   3.000   0.7951   0.00687   0.00190  -0.0848   0.3635   1.0000
   3.250   0.8233   0.00699   0.00198  -0.0848   0.3550   1.0000
   3.500   0.8513   0.00715   0.00208  -0.0847   0.3458   1.0000
   3.750   0.8794   0.00729   0.00218  -0.0847   0.3359   1.0000
   4.000   0.9073   0.00745   0.00229  -0.0847   0.3259   1.0000
   4.250   0.9349   0.00764   0.00242  -0.0846   0.3141   1.0000
   4.500   0.9624   0.00785   0.00256  -0.0846   0.3008   1.0000
   4.750   0.9898   0.00808   0.00271  -0.0845   0.2863   1.0000
   5.000   1.0168   0.00834   0.00289  -0.0844   0.2689   1.0000
   5.250   1.0438   0.00859   0.00307  -0.0843   0.2544   1.0000
   5.500   1.0705   0.00887   0.00328  -0.0841   0.2384   1.0000
   5.750   1.0969   0.00920   0.00351  -0.0840   0.2201   1.0000
   6.000   1.1233   0.00951   0.00374  -0.0838   0.2045   1.0000
   6.250   1.1495   0.00984   0.00400  -0.0836   0.1898   1.0000
   6.500   1.1752   0.01021   0.00428  -0.0834   0.1737   1.0000
   6.750   1.2007   0.01060   0.00459  -0.0831   0.1578   1.0000
   7.000   1.2263   0.01096   0.00489  -0.0829   0.1451   1.0000
   7.250   1.2519   0.01131   0.00519  -0.0826   0.1343   1.0000
   7.500   1.2771   0.01168   0.00551  -0.0823   0.1230   1.0000
   7.750   1.3020   0.01208   0.00585  -0.0820   0.1121   1.0000
   8.000   1.3266   0.01249   0.00621  -0.0817   0.1027   1.0000
   8.250   1.3516   0.01284   0.00655  -0.0813   0.0956   1.0000
   8.500   1.3759   0.01325   0.00692  -0.0809   0.0881   1.0000
   8.750   1.3997   0.01368   0.00732  -0.0805   0.0807   1.0000
   9.000   1.4239   0.01406   0.00769  -0.0801   0.0755   1.0000
   9.250   1.4472   0.01452   0.00812  -0.0796   0.0698   1.0000
   9.500   1.4706   0.01492   0.00853  -0.0791   0.0655   1.0000
   9.750   1.4937   0.01534   0.00896  -0.0785   0.0619   1.0000
  10.000   1.5156   0.01584   0.00944  -0.0779   0.0575   1.0000
  10.250   1.5383   0.01624   0.00987  -0.0773   0.0552   1.0000
  10.500   1.5602   0.01669   0.01034  -0.0766   0.0528   1.0000
  10.750   1.5805   0.01723   0.01088  -0.0757   0.0496   1.0000
  11.000   1.6008   0.01775   0.01141  -0.0748   0.0467   1.0000
  11.250   1.6206   0.01825   0.01194  -0.0739   0.0444   1.0000
  11.500   1.6386   0.01884   0.01255  -0.0728   0.0418   1.0000
  11.750   1.6554   0.01947   0.01319  -0.0714   0.0396   1.0000
  12.000   1.6716   0.02002   0.01378  -0.0700   0.0384   1.0000
  12.250   1.6839   0.02061   0.01442  -0.0679   0.0370   1.0000
  12.500   1.6940   0.02132   0.01517  -0.0657   0.0355   1.0000
  12.750   1.7016   0.02223   0.01610  -0.0634   0.0333   1.0000
  13.000   1.7103   0.02317   0.01708  -0.0615   0.0319   1.0000
  13.250   1.7196   0.02415   0.01812  -0.0598   0.0306   1.0000
  13.500   1.7273   0.02531   0.01933  -0.0582   0.0291   1.0000
  13.750   1.7335   0.02667   0.02073  -0.0567   0.0277   1.0000
  14.000   1.7388   0.02821   0.02231  -0.0553   0.0262   1.0000
  14.250   1.7458   0.02969   0.02387  -0.0543   0.0255   1.0000
  14.500   1.7516   0.03138   0.02563  -0.0533   0.0244   1.0000
  14.750   1.7555   0.03331   0.02762  -0.0525   0.0233   1.0000
  15.000   1.7571   0.03558   0.02994  -0.0518   0.0220   1.0000
  15.250   1.7590   0.03793   0.03236  -0.0514   0.0210   1.0000
  15.500   1.7612   0.04034   0.03486  -0.0511   0.0203   1.0000
  15.750   1.7611   0.04309   0.03768  -0.0510   0.0191   1.0000
  16.000   1.7595   0.04613   0.04079  -0.0511   0.0182   1.0000
  16.250   1.7557   0.04953   0.04426  -0.0514   0.0172   1.0000
  16.500   1.7527   0.05294   0.04776  -0.0518   0.0163   1.0000
  16.750   1.7488   0.05662   0.05153  -0.0525   0.0154   1.0000
  17.000   1.7421   0.06078   0.05578  -0.0535   0.0144   1.0000
  17.250   1.7349   0.06519   0.06028  -0.0547   0.0136   1.0000
  17.500   1.7288   0.06952   0.06471  -0.0559   0.0129   1.0000
  17.750   1.7198   0.07445   0.06973  -0.0576   0.0118   1.0000
  18.000   1.7088   0.07978   0.07514  -0.0594   0.0108   1.0000
  18.250   1.6991   0.08505   0.08051  -0.0614   0.0100   1.0000
  18.500   1.6850   0.09117   0.08673  -0.0639   0.0087   1.0000
  18.750   1.6723   0.09717   0.09283  -0.0664   0.0079   1.0000
  19.000   1.6562   0.10394   0.09970  -0.0694   0.0066   1.0000
  19.250   1.6414   0.11062   0.10648  -0.0726   0.0057   1.0000
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