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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 100,000
Max Cl/Cd: 61.9 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4062-il-100000-n5.txt
Download as CSV file: xf-s4062-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3252   0.10630   0.10162  -0.0448   1.0000   0.0493
  -9.000  -0.3256   0.09978   0.09509  -0.0427   1.0000   0.0291
  -8.750  -0.3329   0.09834   0.09372  -0.0399   1.0000   0.0284
  -8.500  -0.3204   0.09426   0.08965  -0.0433   0.9933   0.0273
  -8.250  -0.3090   0.08950   0.08489  -0.0481   0.9864   0.0259
  -7.750  -0.2918   0.07691   0.07233  -0.0627   0.9699   0.0228
  -7.500  -0.2786   0.07186   0.06728  -0.0692   0.9616   0.0226
  -7.250  -0.2650   0.06643   0.06184  -0.0765   0.9532   0.0223
  -7.000  -0.2484   0.05809   0.05339  -0.0879   0.9452   0.0225
  -6.750  -0.2376   0.05100   0.04612  -0.0948   0.9352   0.0223
  -6.500  -0.2242   0.04363   0.03831  -0.1013   0.9271   0.0224
  -6.250  -0.2087   0.03765   0.03166  -0.1051   0.9193   0.0228
  -6.000  -0.1884   0.03338   0.02670  -0.1070   0.9134   0.0232
  -5.750  -0.1680   0.03054   0.02343  -0.1074   0.9070   0.0236
  -5.500  -0.1414   0.02813   0.02062  -0.1083   0.9030   0.0242
  -5.250  -0.1183   0.02631   0.01845  -0.1081   0.8973   0.0252
  -5.000  -0.0930   0.02469   0.01649  -0.1079   0.8920   0.0264
  -4.750  -0.0644   0.02319   0.01467  -0.1081   0.8884   0.0283
  -4.500  -0.0400   0.02218   0.01350  -0.1078   0.8831   0.0320
  -4.250  -0.0145   0.02131   0.01249  -0.1074   0.8779   0.0364
  -4.000   0.0134   0.02025   0.01130  -0.1075   0.8741   0.0419
  -3.750   0.0393   0.01956   0.01057  -0.1072   0.8693   0.0545
  -3.500   0.0642   0.01900   0.01001  -0.1068   0.8638   0.0773
  -3.250   0.0922   0.01848   0.00952  -0.1070   0.8599   0.1073
  -3.000   0.1197   0.01806   0.00913  -0.1070   0.8559   0.1388
  -2.750   0.1436   0.01781   0.00892  -0.1064   0.8499   0.1703
  -2.500   0.1712   0.01747   0.00862  -0.1064   0.8458   0.2086
  -2.250   0.2001   0.01711   0.00834  -0.1065   0.8427   0.2545
  -2.000   0.2227   0.01697   0.00833  -0.1058   0.8360   0.3047
  -1.750   0.2494   0.01668   0.00819  -0.1056   0.8317   0.3718
  -1.500   0.2772   0.01630   0.00805  -0.1054   0.8285   0.4599
  -1.250   0.2987   0.01610   0.00816  -0.1043   0.8221   0.5621
  -1.000   0.3206   0.01570   0.00815  -0.1025   0.8175   0.6976
  -0.750   0.3601   0.01512   0.00793  -0.1036   0.8150   0.9465
  -0.500   0.3896   0.01524   0.00788  -0.1041   0.8098   1.0000
  -0.250   0.4151   0.01540   0.00789  -0.1037   0.8040   1.0000
   0.000   0.4436   0.01545   0.00779  -0.1037   0.8002   1.0000
   0.250   0.4685   0.01565   0.00788  -0.1033   0.7943   1.0000
   0.500   0.4946   0.01579   0.00793  -0.1030   0.7887   1.0000
   0.750   0.5237   0.01581   0.00783  -0.1029   0.7849   1.0000
   1.000   0.5472   0.01606   0.00804  -0.1023   0.7776   1.0000
   1.250   0.5748   0.01612   0.00803  -0.1021   0.7724   1.0000
   1.500   0.6018   0.01620   0.00806  -0.1018   0.7668   1.0000
   1.750   0.6271   0.01632   0.00816  -0.1013   0.7594   1.0000
   2.000   0.6561   0.01625   0.00803  -0.1011   0.7538   1.0000
   2.500   0.7073   0.01634   0.00811  -0.0998   0.7366   1.0000
   2.750   0.7344   0.01628   0.00805  -0.0993   0.7281   1.0000
   3.000   0.7593   0.01635   0.00813  -0.0986   0.7182   1.0000
   3.250   0.7877   0.01624   0.00803  -0.0982   0.7102   1.0000
   3.500   0.8126   0.01631   0.00814  -0.0975   0.6996   1.0000
   3.750   0.8376   0.01637   0.00824  -0.0968   0.6887   1.0000
   4.000   0.8638   0.01637   0.00828  -0.0961   0.6779   1.0000
   4.250   0.8904   0.01635   0.00831  -0.0955   0.6664   1.0000
   4.500   0.9162   0.01636   0.00836  -0.0948   0.6534   1.0000
   4.750   0.9408   0.01642   0.00848  -0.0940   0.6385   1.0000
   5.000   0.9645   0.01654   0.00869  -0.0931   0.6212   1.0000
   5.250   0.9884   0.01663   0.00884  -0.0921   0.6018   1.0000
   5.500   1.0128   0.01671   0.00893  -0.0911   0.5801   1.0000
   5.750   1.0356   0.01687   0.00910  -0.0900   0.5535   1.0000
   6.000   1.0578   0.01709   0.00931  -0.0887   0.5216   1.0000
   6.250   1.0786   0.01743   0.00955  -0.0873   0.4834   1.0000
   6.500   1.0975   0.01792   0.00988  -0.0856   0.4412   1.0000
   6.750   1.1143   0.01860   0.01036  -0.0838   0.3994   1.0000
   7.000   1.1296   0.01940   0.01100  -0.0819   0.3609   1.0000
   7.250   1.1443   0.02025   0.01170  -0.0799   0.3264   1.0000
   7.500   1.1583   0.02113   0.01247  -0.0780   0.2955   1.0000
   7.750   1.1721   0.02203   0.01327  -0.0761   0.2677   1.0000
   8.000   1.1854   0.02294   0.01412  -0.0742   0.2430   1.0000
   8.250   1.1974   0.02386   0.01499  -0.0721   0.2206   1.0000
   8.500   1.2091   0.02478   0.01592  -0.0700   0.2005   1.0000
   8.750   1.2205   0.02577   0.01690  -0.0680   0.1813   1.0000
   9.000   1.2310   0.02684   0.01795  -0.0659   0.1639   1.0000
   9.250   1.2414   0.02796   0.01908  -0.0640   0.1465   1.0000
   9.500   1.2513   0.02917   0.02030  -0.0621   0.1286   1.0000
   9.750   1.2595   0.03052   0.02159  -0.0603   0.1109   1.0000
  10.000   1.2674   0.03196   0.02300  -0.0585   0.0935   1.0000
  10.250   1.2754   0.03345   0.02449  -0.0568   0.0792   1.0000
  10.500   1.2823   0.03508   0.02614  -0.0552   0.0682   1.0000
  10.750   1.2872   0.03692   0.02799  -0.0534   0.0598   1.0000
  11.000   1.2933   0.03873   0.02993  -0.0518   0.0524   1.0000
  11.250   1.2960   0.04088   0.03213  -0.0502   0.0468   1.0000
  11.500   1.2997   0.04300   0.03436  -0.0488   0.0416   1.0000
  11.750   1.2998   0.04550   0.03692  -0.0474   0.0382   1.0000
  12.000   1.3029   0.04785   0.03949  -0.0461   0.0352   1.0000
  12.250   1.3044   0.05039   0.04217  -0.0450   0.0330   1.0000
  12.500   1.3046   0.05313   0.04502  -0.0441   0.0315   1.0000
  12.750   1.3027   0.05621   0.04818  -0.0432   0.0302   1.0000
  13.000   1.3059   0.05894   0.05113  -0.0424   0.0290   1.0000
  13.250   1.3078   0.06185   0.05426  -0.0418   0.0276   1.0000
  13.500   1.3081   0.06495   0.05755  -0.0414   0.0263   1.0000
  13.750   1.3072   0.06821   0.06098  -0.0413   0.0253   1.0000
  14.000   1.3047   0.07174   0.06464  -0.0415   0.0243   1.0000
  14.250   1.3020   0.07544   0.06845  -0.0418   0.0236   1.0000
  14.500   1.2994   0.07935   0.07249  -0.0420   0.0231   1.0000
  14.750   1.2949   0.08373   0.07712  -0.0427   0.0227   1.0000
  15.000   1.2879   0.08865   0.08232  -0.0439   0.0224   1.0000
  15.250   1.2791   0.09400   0.08797  -0.0455   0.0221   1.0000
  15.500   1.2680   0.09994   0.09417  -0.0478   0.0219   1.0000
  15.750   1.2548   0.10652   0.10101  -0.0508   0.0217   1.0000
  16.000   1.2398   0.11380   0.10853  -0.0546   0.0217   1.0000
  16.250   1.2231   0.12182   0.11679  -0.0592   0.0217   1.0000
  16.500   1.2045   0.13081   0.12596  -0.0648   0.0217   1.0000
  16.750   1.1841   0.14090   0.13625  -0.0714   0.0219   1.0000
  17.000   1.1616   0.15234   0.14785  -0.0790   0.0222   1.0000
  17.250   1.1370   0.16537   0.16099  -0.0875   0.0225   1.0000
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