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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 50,000
Max Cl/Cd: 28.35 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4180-il-50000.txt
Download as CSV file: xf-s4180-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2839   0.10484   0.09823  -0.0214   1.0000   0.1803
  -8.000  -0.2870   0.10353   0.09703  -0.0227   1.0000   0.1873
  -7.750  -0.3118   0.10500   0.09873  -0.0249   1.0000   0.1893
  -7.500  -0.2724   0.09715   0.09081  -0.0224   1.0000   0.1986
  -7.250  -0.2897   0.09729   0.09116  -0.0231   1.0000   0.2045
  -7.000  -0.2758   0.09293   0.08686  -0.0220   1.0000   0.2101
  -6.750  -0.2796   0.09133   0.08540  -0.0205   1.0000   0.2177
  -6.500  -0.3112   0.09254   0.08686  -0.0202   1.0000   0.2213
  -6.250  -0.2956   0.08804   0.08242  -0.0163   1.0000   0.2278
  -6.000  -0.3110   0.08738   0.08190  -0.0139   1.0000   0.2343
  -5.750  -0.3452   0.08881   0.08350  -0.0155   1.0000   0.2379
  -5.250  -0.3525   0.08444   0.07931  -0.0097   1.0000   0.2531
  -5.000  -0.3543   0.08179   0.07676  -0.0062   1.0000   0.2586
  -4.750  -0.3662   0.08107   0.07610  -0.0090   1.0000   0.2709
  -4.500  -0.3638   0.07831   0.07343  -0.0033   1.0000   0.2779
  -4.250  -0.3677   0.07644   0.07163  -0.0031   1.0000   0.2910
  -4.000  -0.3689   0.07454   0.06979  -0.0023   1.0000   0.3067
  -3.750  -0.3687   0.07260   0.06792  -0.0005   1.0000   0.3243
  -3.500  -0.3678   0.07078   0.06615   0.0012   1.0000   0.3449
  -3.250  -0.3371   0.06822   0.06357  -0.0032   0.9887   0.3992
  -3.000  -0.3133   0.06494   0.06035  -0.0003   0.9782   0.4383
  -2.750  -0.1239   0.04836   0.04174  -0.0641   0.9657   0.1900
  -2.500  -0.0549   0.04251   0.03501  -0.0740   0.9567   0.1550
  -2.250  -0.0062   0.03944   0.03145  -0.0792   0.9448   0.1522
  -2.000   0.0430   0.03683   0.02821  -0.0837   0.9330   0.1504
  -1.750   0.0923   0.03494   0.02567  -0.0878   0.9215   0.1586
  -1.500   0.1423   0.03337   0.02388  -0.0917   0.9104   0.1777
  -1.250   0.1815   0.03230   0.02268  -0.0937   0.8974   0.2099
  -1.000   0.2176   0.03149   0.02184  -0.0951   0.8847   0.2560
  -0.750   0.2577   0.03064   0.02115  -0.0969   0.8727   0.3224
  -0.500   0.2997   0.02807   0.02049  -0.0978   0.8642   0.6360
  -0.250   0.3331   0.02791   0.02002  -0.0976   0.8504   1.0000
   0.000   0.3647   0.02859   0.02027  -0.0985   0.8368   1.0000
   0.250   0.3966   0.02927   0.02064  -0.0995   0.8239   1.0000
   0.500   0.4321   0.02986   0.02094  -0.1007   0.8120   1.0000
   0.750   0.4696   0.03034   0.02118  -0.1020   0.8007   1.0000
   1.000   0.4910   0.03123   0.02191  -0.1015   0.7873   1.0000
   1.250   0.5151   0.03211   0.02263  -0.1013   0.7748   1.0000
   1.500   0.5450   0.03281   0.02319  -0.1016   0.7638   1.0000
   1.750   0.5786   0.03330   0.02355  -0.1021   0.7532   1.0000
   2.000   0.5954   0.03451   0.02467  -0.1013   0.7404   1.0000
   2.250   0.6169   0.03556   0.02564  -0.1009   0.7287   1.0000
   2.500   0.6568   0.03570   0.02569  -0.1014   0.7201   1.0000
   2.750   0.6707   0.03716   0.02711  -0.1006   0.7073   1.0000
   3.000   0.6863   0.03860   0.02853  -0.0998   0.6952   1.0000
   3.250   0.7117   0.03951   0.02940  -0.0995   0.6849   1.0000
   3.500   0.7418   0.04008   0.02994  -0.0992   0.6746   1.0000
   3.750   0.7519   0.04198   0.03184  -0.0983   0.6621   1.0000
   4.000   0.7687   0.04345   0.03333  -0.0976   0.6505   1.0000
   4.250   0.8117   0.04307   0.03295  -0.0974   0.6420   1.0000
   4.500   0.8179   0.04532   0.03522  -0.0964   0.6286   1.0000
   4.750   0.8260   0.04750   0.03742  -0.0956   0.6160   1.0000
   5.000   0.8442   0.04892   0.03890  -0.0948   0.6041   1.0000
   5.250   0.8925   0.04781   0.03783  -0.0940   0.5949   1.0000
   5.500   0.8970   0.05032   0.04038  -0.0931   0.5810   1.0000
   5.750   0.9018   0.05285   0.04296  -0.0921   0.5674   1.0000
   6.000   0.9093   0.05510   0.04528  -0.0911   0.5541   1.0000
   6.250   0.9253   0.05662   0.04686  -0.0900   0.5412   1.0000
   6.500   0.9666   0.05578   0.04612  -0.0886   0.5289   1.0000
   6.750   1.0162   0.05368   0.04416  -0.0867   0.5170   1.0000
   7.000   1.0260   0.05560   0.04616  -0.0854   0.5022   1.0000
   7.250   1.0392   0.05710   0.04775  -0.0839   0.4873   1.0000
   7.500   1.0530   0.05851   0.04925  -0.0824   0.4724   1.0000
   7.750   1.0752   0.05887   0.04975  -0.0806   0.4574   1.0000
   8.000   1.1085   0.05788   0.04887  -0.0784   0.4421   1.0000
   8.250   1.1677   0.05372   0.04486  -0.0757   0.4259   1.0000
   8.500   1.2447   0.04769   0.03878  -0.0736   0.4075   1.0000
   8.750   1.2492   0.04962   0.04088  -0.0716   0.3894   1.0000
   9.000   1.2655   0.05019   0.04157  -0.0695   0.3705   1.0000
   9.250   1.3157   0.04721   0.03848  -0.0679   0.3486   1.0000
   9.500   1.3388   0.04723   0.03849  -0.0661   0.3289   1.0000
   9.750   1.3504   0.04850   0.03989  -0.0641   0.3108   1.0000
  10.000   1.3686   0.04923   0.04063  -0.0624   0.2928   1.0000
  10.250   1.3868   0.05021   0.04162  -0.0608   0.2764   1.0000
  10.500   1.3997   0.05173   0.04319  -0.0591   0.2618   1.0000
  10.750   1.4055   0.05405   0.04564  -0.0573   0.2499   1.0000
  11.000   1.4177   0.05612   0.04777  -0.0558   0.2388   1.0000
  11.250   1.4404   0.05746   0.04905  -0.0548   0.2267   1.0000
  11.500   1.4037   0.06294   0.05493  -0.0520   0.2243   1.0000
  11.750   1.3531   0.07002   0.06226  -0.0504   0.2246   1.0000
  12.000   1.2847   0.08152   0.07387  -0.0530   0.2270   1.0000
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