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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 500,000
Max Cl/Cd: 104.39 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4180-il-500000-n5.txt
Download as CSV file: xf-s4180-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3305   0.10360   0.10127  -0.0214   1.0000   0.0142
  -9.500  -0.3277   0.09954   0.09723  -0.0233   1.0000   0.0135
  -9.250  -0.3220   0.09641   0.09411  -0.0245   1.0000   0.0134
  -9.000  -0.3163   0.09342   0.09114  -0.0256   1.0000   0.0132
  -8.750  -0.3118   0.09030   0.08805  -0.0269   1.0000   0.0130
  -8.500  -0.3015   0.08592   0.08368  -0.0309   0.9690   0.0129
  -8.250  -0.2808   0.07969   0.07739  -0.0395   0.9356   0.0131
  -8.000  -0.2709   0.07577   0.07337  -0.0432   0.9012   0.0129
  -7.750  -0.2722   0.07221   0.06973  -0.0446   0.8726   0.0129
  -6.750  -0.2955   0.02047   0.01574  -0.0857   0.8043   0.0134
  -6.500  -0.2701   0.01875   0.01363  -0.0860   0.7930   0.0136
  -6.250  -0.2438   0.01757   0.01213  -0.0861   0.7818   0.0137
  -6.000  -0.2176   0.01612   0.01040  -0.0863   0.7703   0.0140
  -5.750  -0.1907   0.01521   0.00931  -0.0863   0.7587   0.0143
  -5.500  -0.1634   0.01451   0.00847  -0.0863   0.7476   0.0145
  -5.250  -0.1360   0.01391   0.00771  -0.0862   0.7359   0.0148
  -5.000  -0.1083   0.01335   0.00702  -0.0862   0.7241   0.0151
  -4.750  -0.0804   0.01286   0.00640  -0.0861   0.7124   0.0155
  -4.500  -0.0525   0.01244   0.00586  -0.0860   0.7010   0.0161
  -4.000   0.0037   0.01168   0.00485  -0.0858   0.6772   0.0170
  -3.750   0.0319   0.01134   0.00441  -0.0858   0.6659   0.0173
  -3.500   0.0601   0.01090   0.00388  -0.0857   0.6548   0.0178
  -3.250   0.0883   0.01061   0.00352  -0.0857   0.6430   0.0185
  -3.000   0.1168   0.01038   0.00323  -0.0857   0.6317   0.0192
  -2.750   0.1452   0.01019   0.00295  -0.0856   0.6211   0.0200
  -2.500   0.1736   0.01003   0.00271  -0.0855   0.6099   0.0209
  -2.250   0.2022   0.00986   0.00248  -0.0855   0.5987   0.0224
  -2.000   0.2307   0.00971   0.00230  -0.0855   0.5884   0.0249
  -1.750   0.2591   0.00959   0.00213  -0.0854   0.5779   0.0293
  -1.500   0.2876   0.00944   0.00201  -0.0854   0.5671   0.0423
  -1.250   0.3161   0.00936   0.00192  -0.0854   0.5572   0.0568
  -1.000   0.3445   0.00931   0.00186  -0.0854   0.5472   0.0695
  -0.750   0.3730   0.00923   0.00181  -0.0854   0.5371   0.0865
  -0.500   0.4014   0.00918   0.00178  -0.0854   0.5278   0.1080
  -0.250   0.4298   0.00912   0.00175  -0.0854   0.5181   0.1330
   0.000   0.4583   0.00902   0.00174  -0.0855   0.5090   0.1740
   0.250   0.4866   0.00890   0.00175  -0.0856   0.5003   0.2366
   0.500   0.5151   0.00876   0.00177  -0.0857   0.4913   0.3081
   0.750   0.5433   0.00859   0.00182  -0.0858   0.4830   0.4054
   1.000   0.5714   0.00832   0.00189  -0.0859   0.4745   0.5444
   1.250   0.5979   0.00795   0.00200  -0.0856   0.4666   0.7234
   1.500   0.6155   0.00752   0.00205  -0.0828   0.4590   0.9265
   1.750   0.6473   0.00758   0.00206  -0.0835   0.4509   1.0000
   2.000   0.6756   0.00771   0.00211  -0.0834   0.4425   1.0000
   2.250   0.7039   0.00784   0.00218  -0.0834   0.4346   1.0000
   2.500   0.7320   0.00797   0.00225  -0.0834   0.4261   1.0000
   2.750   0.7601   0.00811   0.00233  -0.0833   0.4177   1.0000
   3.000   0.7880   0.00827   0.00243  -0.0833   0.4087   1.0000
   3.250   0.8161   0.00840   0.00252  -0.0832   0.3998   1.0000
   3.500   0.8438   0.00858   0.00263  -0.0831   0.3908   1.0000
   3.750   0.8716   0.00873   0.00275  -0.0831   0.3814   1.0000
   4.000   0.8993   0.00890   0.00288  -0.0830   0.3724   1.0000
   4.250   0.9268   0.00909   0.00302  -0.0829   0.3627   1.0000
   4.500   0.9543   0.00926   0.00316  -0.0828   0.3528   1.0000
   4.750   0.9816   0.00946   0.00332  -0.0827   0.3423   1.0000
   5.000   1.0086   0.00969   0.00350  -0.0826   0.3303   1.0000
   5.250   1.0355   0.00992   0.00368  -0.0824   0.3172   1.0000
   5.500   1.0622   0.01018   0.00389  -0.0823   0.3028   1.0000
   5.750   1.0885   0.01047   0.00411  -0.0821   0.2870   1.0000
   6.250   1.1407   0.01110   0.00462  -0.0817   0.2560   1.0000
   6.500   1.1662   0.01147   0.00492  -0.0814   0.2382   1.0000
   6.750   1.1914   0.01187   0.00524  -0.0811   0.2207   1.0000
   7.000   1.2163   0.01228   0.00559  -0.0808   0.2043   1.0000
   7.250   1.2406   0.01275   0.00598  -0.0804   0.1870   1.0000
   7.500   1.2645   0.01326   0.00640  -0.0800   0.1700   1.0000
   7.750   1.2883   0.01374   0.00683  -0.0795   0.1555   1.0000
   8.250   1.3353   0.01474   0.00773  -0.0786   0.1305   1.0000
   8.500   1.3582   0.01525   0.00821  -0.0780   0.1191   1.0000
   8.750   1.3810   0.01576   0.00870  -0.0775   0.1099   1.0000
   9.000   1.4030   0.01631   0.00922  -0.0768   0.1015   1.0000
   9.250   1.4249   0.01684   0.00975  -0.0761   0.0937   1.0000
   9.500   1.4462   0.01739   0.01030  -0.0754   0.0869   1.0000
   9.750   1.4666   0.01799   0.01089  -0.0746   0.0807   1.0000
  10.000   1.4869   0.01856   0.01148  -0.0737   0.0759   1.0000
  10.250   1.5062   0.01916   0.01211  -0.0727   0.0711   1.0000
  10.500   1.5240   0.01985   0.01280  -0.0716   0.0670   1.0000
  10.750   1.5424   0.02042   0.01344  -0.0705   0.0642   1.0000
  11.000   1.5584   0.02111   0.01416  -0.0691   0.0609   1.0000
  11.250   1.5701   0.02188   0.01496  -0.0671   0.0580   1.0000
  11.500   1.5811   0.02264   0.01577  -0.0650   0.0560   1.0000
  11.750   1.5922   0.02342   0.01663  -0.0631   0.0543   1.0000
  12.000   1.6017   0.02436   0.01764  -0.0613   0.0525   1.0000
  12.250   1.6097   0.02547   0.01880  -0.0595   0.0505   1.0000
  12.500   1.6157   0.02682   0.02019  -0.0578   0.0482   1.0000
  12.750   1.6237   0.02810   0.02154  -0.0565   0.0465   1.0000
  13.000   1.6319   0.02944   0.02297  -0.0553   0.0447   1.0000
  13.250   1.6383   0.03103   0.02463  -0.0543   0.0428   1.0000
  13.500   1.6426   0.03289   0.02655  -0.0533   0.0412   1.0000
  13.750   1.6455   0.03500   0.02873  -0.0525   0.0397   1.0000
  14.000   1.6498   0.03706   0.03088  -0.0520   0.0387   1.0000
  14.250   1.6543   0.03919   0.03312  -0.0516   0.0377   1.0000
  14.500   1.6574   0.04155   0.03557  -0.0513   0.0365   1.0000
  14.750   1.6588   0.04419   0.03829  -0.0512   0.0353   1.0000
  15.000   1.6582   0.04713   0.04131  -0.0513   0.0339   1.0000
  15.250   1.6558   0.05041   0.04467  -0.0517   0.0328   1.0000
  15.500   1.6538   0.05375   0.04811  -0.0521   0.0319   1.0000
  15.750   1.6531   0.05697   0.05145  -0.0526   0.0311   1.0000
  16.000   1.6510   0.06049   0.05509  -0.0533   0.0301   1.0000
  16.250   1.6478   0.06429   0.05897  -0.0543   0.0290   1.0000
  16.500   1.6432   0.06836   0.06314  -0.0554   0.0281   1.0000
  16.750   1.6372   0.07278   0.06765  -0.0567   0.0272   1.0000
  17.000   1.6293   0.07759   0.07256  -0.0583   0.0263   1.0000
  17.250   1.6249   0.08197   0.07705  -0.0598   0.0257   1.0000
  17.500   1.6196   0.08656   0.08176  -0.0615   0.0249   1.0000
  17.750   1.6134   0.09141   0.08672  -0.0634   0.0241   1.0000
  18.000   1.6062   0.09647   0.09189  -0.0654   0.0233   1.0000
  18.250   1.5979   0.10184   0.09735  -0.0677   0.0225   1.0000
  18.500   1.5887   0.10744   0.10305  -0.0702   0.0218   1.0000
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