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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 50,000
Max Cl/Cd: 37.71 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4180-il-50000-n5.txt
Download as CSV file: xf-s4180-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3009   0.11136   0.10444  -0.0227   1.0000   0.1052
  -8.750  -0.3053   0.10998   0.10317  -0.0254   1.0000   0.1085
  -8.500  -0.3139   0.10897   0.10230  -0.0285   1.0000   0.1095
  -8.000  -0.2858   0.10016   0.09356  -0.0271   1.0000   0.1135
  -7.750  -0.2802   0.09734   0.09082  -0.0273   1.0000   0.1155
  -7.500  -0.2776   0.09481   0.08838  -0.0277   1.0000   0.1173
  -7.250  -0.2786   0.09255   0.08625  -0.0278   1.0000   0.1189
  -7.000  -0.2838   0.09062   0.08447  -0.0275   1.0000   0.1200
  -6.750  -0.2898   0.08867   0.08267  -0.0271   1.0000   0.1204
  -6.500  -0.2969   0.08673   0.08087  -0.0263   1.0000   0.1199
  -6.000  -0.3225   0.07840   0.07264  -0.0318   1.0000   0.0695
  -5.750  -0.2927   0.07331   0.06745  -0.0383   0.9880   0.0638
  -5.500  -0.2611   0.06732   0.06134  -0.0475   0.9752   0.0605
  -5.250  -0.2258   0.06055   0.05434  -0.0582   0.9627   0.0585
  -5.000  -0.1909   0.05566   0.04925  -0.0654   0.9515   0.0594
  -4.750  -0.1505   0.05030   0.04355  -0.0734   0.9421   0.0599
  -4.500  -0.1138   0.04516   0.03796  -0.0797   0.9304   0.0593
  -4.250  -0.0764   0.04071   0.03299  -0.0847   0.9196   0.0591
  -4.000  -0.0359   0.03696   0.02870  -0.0891   0.9107   0.0599
  -3.750  -0.0019   0.03429   0.02557  -0.0913   0.8987   0.0620
  -3.500   0.0332   0.03184   0.02249  -0.0932   0.8872   0.0661
  -3.250   0.0688   0.02974   0.01997  -0.0948   0.8769   0.0693
  -3.000   0.1013   0.02824   0.01824  -0.0955   0.8655   0.0731
  -2.750   0.1321   0.02698   0.01653  -0.0956   0.8530   0.0804
  -2.500   0.1615   0.02597   0.01550  -0.0956   0.8410   0.0893
  -2.250   0.1924   0.02500   0.01438  -0.0956   0.8302   0.1033
  -2.000   0.2211   0.02427   0.01346  -0.0952   0.8179   0.1248
  -1.750   0.2486   0.02360   0.01282  -0.0949   0.8052   0.1511
  -1.500   0.2767   0.02296   0.01218  -0.0945   0.7932   0.1830
  -1.250   0.3055   0.02227   0.01157  -0.0942   0.7824   0.2263
  -1.000   0.3322   0.02156   0.01120  -0.0939   0.7702   0.3044
  -0.750   0.3531   0.02046   0.01112  -0.0923   0.7581   0.5315
  -0.500   0.3776   0.01943   0.01076  -0.0895   0.7469   1.0000
  -0.250   0.4066   0.01955   0.01047  -0.0891   0.7364   1.0000
   0.000   0.4332   0.01978   0.01040  -0.0887   0.7236   1.0000
   0.250   0.4601   0.02002   0.01036  -0.0883   0.7117   1.0000
   0.500   0.4876   0.02022   0.01030  -0.0879   0.7009   1.0000
   0.750   0.5151   0.02041   0.01027  -0.0874   0.6902   1.0000
   1.000   0.5412   0.02072   0.01040  -0.0870   0.6783   1.0000
   1.250   0.5681   0.02099   0.01049  -0.0866   0.6675   1.0000
   1.500   0.5958   0.02119   0.01051  -0.0861   0.6580   1.0000
   1.750   0.6215   0.02156   0.01077  -0.0857   0.6463   1.0000
   2.000   0.6479   0.02188   0.01097  -0.0853   0.6358   1.0000
   2.250   0.6754   0.02212   0.01107  -0.0848   0.6267   1.0000
   2.500   0.7006   0.02255   0.01146  -0.0844   0.6153   1.0000
   2.750   0.7270   0.02290   0.01172  -0.0839   0.6055   1.0000
   3.000   0.7537   0.02321   0.01195  -0.0835   0.5961   1.0000
   3.250   0.7786   0.02369   0.01243  -0.0830   0.5853   1.0000
   3.500   0.8053   0.02402   0.01269  -0.0825   0.5763   1.0000
   3.750   0.8307   0.02446   0.01311  -0.0821   0.5661   1.0000
   4.000   0.8555   0.02496   0.01361  -0.0816   0.5558   1.0000
   4.250   0.8829   0.02521   0.01381  -0.0810   0.5475   1.0000
   4.500   0.9062   0.02582   0.01449  -0.0805   0.5362   1.0000
   4.750   0.9310   0.02630   0.01499  -0.0800   0.5261   1.0000
   5.000   0.9576   0.02659   0.01528  -0.0794   0.5170   1.0000
   5.250   0.9803   0.02722   0.01599  -0.0788   0.5054   1.0000
   5.500   1.0045   0.02770   0.01652  -0.0781   0.4948   1.0000
   5.750   1.0311   0.02794   0.01675  -0.0774   0.4852   1.0000
   6.000   1.0529   0.02857   0.01750  -0.0766   0.4728   1.0000
   6.250   1.0754   0.02913   0.01814  -0.0759   0.4609   1.0000
   6.500   1.0991   0.02955   0.01861  -0.0750   0.4493   1.0000
   6.750   1.1240   0.02982   0.01892  -0.0742   0.4379   1.0000
   7.000   1.1453   0.03037   0.01958  -0.0733   0.4247   1.0000
   7.250   1.1658   0.03095   0.02027  -0.0722   0.4110   1.0000
   7.500   1.1862   0.03150   0.02092  -0.0712   0.3971   1.0000
   7.750   1.2059   0.03204   0.02159  -0.0700   0.3829   1.0000
   8.000   1.2250   0.03260   0.02224  -0.0688   0.3681   1.0000
   8.250   1.2430   0.03320   0.02293  -0.0675   0.3527   1.0000
   8.500   1.2598   0.03386   0.02367  -0.0661   0.3369   1.0000
   8.750   1.2750   0.03459   0.02450  -0.0646   0.3207   1.0000
   9.000   1.2891   0.03539   0.02537  -0.0630   0.3045   1.0000
   9.250   1.3015   0.03630   0.02631  -0.0613   0.2883   1.0000
   9.500   1.3120   0.03736   0.02740  -0.0596   0.2726   1.0000
   9.750   1.3202   0.03858   0.02865  -0.0578   0.2572   1.0000
  10.000   1.3249   0.04000   0.03010  -0.0557   0.2430   1.0000
  10.250   1.3278   0.04166   0.03180  -0.0537   0.2298   1.0000
  10.500   1.3301   0.04352   0.03371  -0.0521   0.2173   1.0000
  10.750   1.3319   0.04554   0.03577  -0.0506   0.2060   1.0000
  11.000   1.3347   0.04760   0.03783  -0.0494   0.1958   1.0000
  11.250   1.3370   0.04980   0.04008  -0.0483   0.1863   1.0000
  11.500   1.3374   0.05245   0.04285  -0.0476   0.1773   1.0000
  11.750   1.3415   0.05469   0.04505  -0.0468   0.1693   1.0000
  12.000   1.3403   0.05771   0.04826  -0.0465   0.1618   1.0000
  12.250   1.3461   0.05997   0.05049  -0.0458   0.1553   1.0000
  12.500   1.3430   0.06351   0.05427  -0.0459   0.1490   1.0000
  12.750   1.3514   0.06548   0.05617  -0.0453   0.1430   1.0000
  13.000   1.3436   0.06985   0.06086  -0.0459   0.1381   1.0000
  13.250   1.3414   0.07351   0.06467  -0.0463   0.1334   1.0000
  13.500   1.3538   0.07517   0.06628  -0.0456   0.1287   1.0000
  13.750   1.3372   0.08117   0.07264  -0.0474   0.1257   1.0000
  14.000   1.3218   0.08719   0.07892  -0.0494   0.1226   1.0000
  14.250   1.3145   0.09204   0.08392  -0.0510   0.1193   1.0000
  14.500   1.3277   0.09347   0.08531  -0.0503   0.1153   1.0000
  14.750   1.2909   0.10380   0.09598  -0.0555   0.1140   1.0000
  15.000   1.2292   0.12056   0.11305  -0.0651   0.1133   1.0000
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