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S2062 8% (s2062-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 50,000
Max Cl/Cd: 36.42 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2062-il-50000-n5.txt
Download as CSV file: xf-s2062-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2062 8%                                        
  
 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  -0.4973   0.09504   0.08791  -0.0231   1.0000   0.0409
  -8.750  -0.4988   0.09070   0.08365  -0.0251   1.0000   0.0403
  -8.500  -0.5020   0.08619   0.07923  -0.0274   1.0000   0.0398
  -8.250  -0.5067   0.08167   0.07481  -0.0299   1.0000   0.0393
  -8.000  -0.5132   0.07668   0.06991  -0.0333   1.0000   0.0385
  -7.750  -0.5182   0.07100   0.06426  -0.0372   1.0000   0.0379
  -7.500  -0.5230   0.06540   0.05862  -0.0402   1.0000   0.0373
  -7.250  -0.5264   0.06000   0.05309  -0.0424   1.0000   0.0367
  -7.000  -0.5269   0.05485   0.04771  -0.0437   1.0000   0.0365
  -6.750  -0.5234   0.05002   0.04255  -0.0443   1.0000   0.0364
  -6.500  -0.5156   0.04570   0.03785  -0.0443   1.0000   0.0366
  -6.250  -0.5042   0.04177   0.03349  -0.0440   1.0000   0.0372
  -6.000  -0.4895   0.03847   0.02975  -0.0434   1.0000   0.0389
  -5.750  -0.4724   0.03537   0.02611  -0.0427   1.0000   0.0422
  -5.500  -0.4524   0.03239   0.02237  -0.0417   1.0000   0.0455
  -5.250  -0.4334   0.03020   0.02012  -0.0408   1.0000   0.0490
  -5.000  -0.4119   0.02806   0.01763  -0.0396   1.0000   0.0543
  -4.750  -0.3909   0.02652   0.01594  -0.0386   1.0000   0.0650
  -4.500  -0.3690   0.02500   0.01412  -0.0374   1.0000   0.0825
  -4.250  -0.3478   0.02370   0.01286  -0.0364   1.0000   0.1047
  -4.000  -0.3258   0.02255   0.01167  -0.0354   1.0000   0.1314
  -3.750  -0.3033   0.02153   0.01061  -0.0346   1.0000   0.1600
  -3.500  -0.2811   0.02064   0.00977  -0.0338   1.0000   0.1969
  -3.250  -0.2590   0.01978   0.00904  -0.0330   1.0000   0.2418
  -3.000  -0.2372   0.01896   0.00839  -0.0323   1.0000   0.3057
  -2.750  -0.2164   0.01813   0.00796  -0.0313   1.0000   0.3946
  -2.500  -0.1981   0.01733   0.00770  -0.0294   1.0000   0.5170
  -2.250  -0.1851   0.01672   0.00771  -0.0254   1.0000   0.6657
  -2.000  -0.1704   0.01643   0.00768  -0.0213   1.0000   0.8125
  -1.750  -0.1181   0.01613   0.00720  -0.0252   1.0000   1.0000
  -1.500  -0.0992   0.01616   0.00692  -0.0244   1.0000   1.0000
  -1.250  -0.0793   0.01622   0.00672  -0.0236   1.0000   1.0000
  -1.000  -0.0590   0.01633   0.00659  -0.0229   1.0000   1.0000
  -0.750  -0.0384   0.01648   0.00649  -0.0223   1.0000   1.0000
  -0.500  -0.0177   0.01665   0.00649  -0.0217   1.0000   1.0000
  -0.250   0.0030   0.01687   0.00655  -0.0212   1.0000   1.0000
   0.000   0.0390   0.01722   0.00675  -0.0236   0.9924   1.0000
   0.250   0.0809   0.01763   0.00701  -0.0271   0.9819   1.0000
   0.500   0.1224   0.01799   0.00728  -0.0304   0.9707   1.0000
   0.750   0.1623   0.01830   0.00753  -0.0333   0.9584   1.0000
   1.000   0.2019   0.01858   0.00779  -0.0360   0.9455   1.0000
   1.250   0.2417   0.01882   0.00803  -0.0387   0.9321   1.0000
   1.500   0.2817   0.01902   0.00826  -0.0412   0.9182   1.0000
   1.750   0.3222   0.01916   0.00849  -0.0437   0.9037   1.0000
   2.000   0.3631   0.01926   0.00867  -0.0461   0.8889   1.0000
   2.250   0.4028   0.01929   0.00880  -0.0480   0.8731   1.0000
   2.500   0.4368   0.01931   0.00898  -0.0487   0.8543   1.0000
   2.750   0.4713   0.01927   0.00908  -0.0494   0.8346   1.0000
   3.000   0.5053   0.01920   0.00914  -0.0497   0.8138   1.0000
   3.250   0.5368   0.01913   0.00922  -0.0495   0.7903   1.0000
   3.500   0.5663   0.01907   0.00936  -0.0489   0.7639   1.0000
   3.750   0.5957   0.01901   0.00944  -0.0481   0.7348   1.0000
   4.000   0.6237   0.01899   0.00953  -0.0470   0.7015   1.0000
   4.250   0.6510   0.01902   0.00970  -0.0458   0.6637   1.0000
   4.500   0.6768   0.01916   0.00986  -0.0443   0.6205   1.0000
   4.750   0.7004   0.01944   0.01013  -0.0426   0.5715   1.0000
   5.000   0.7229   0.01985   0.01047  -0.0408   0.5187   1.0000
   5.250   0.7436   0.02044   0.01094  -0.0389   0.4620   1.0000
   5.500   0.7629   0.02118   0.01154  -0.0371   0.4022   1.0000
   5.750   0.7804   0.02211   0.01232  -0.0352   0.3381   1.0000
   6.000   0.7964   0.02326   0.01318  -0.0335   0.2683   1.0000
   6.250   0.8107   0.02477   0.01423  -0.0319   0.1885   1.0000
   6.500   0.8254   0.02665   0.01556  -0.0307   0.1145   1.0000
   6.750   0.8419   0.02866   0.01734  -0.0294   0.0820   1.0000
   7.000   0.8593   0.03059   0.01927  -0.0280   0.0687   1.0000
   7.250   0.8792   0.03244   0.02131  -0.0266   0.0607   1.0000
   7.500   0.8982   0.03433   0.02323  -0.0255   0.0544   1.0000
   7.750   0.9198   0.03621   0.02551  -0.0245   0.0489   1.0000
   8.000   0.9408   0.03840   0.02789  -0.0236   0.0461   1.0000
   8.250   0.9614   0.04112   0.03073  -0.0228   0.0441   1.0000
   8.500   0.9810   0.04418   0.03419  -0.0217   0.0429   1.0000
   8.750   0.9963   0.04750   0.03804  -0.0204   0.0421   1.0000
   9.000   1.0066   0.05117   0.04222  -0.0189   0.0415   1.0000
   9.250   1.0114   0.05503   0.04658  -0.0172   0.0409   1.0000
   9.500   1.0103   0.05898   0.05099  -0.0155   0.0403   1.0000
   9.750   1.0041   0.06297   0.05537  -0.0139   0.0397   1.0000
  10.000   0.9922   0.06695   0.05967  -0.0124   0.0393   1.0000
  10.250   0.9754   0.07102   0.06397  -0.0111   0.0394   1.0000
  10.500   0.9559   0.07565   0.06880  -0.0113   0.0396   1.0000
  10.750   0.9348   0.08118   0.07448  -0.0134   0.0400   1.0000
  11.000   0.9141   0.08771   0.08111  -0.0171   0.0407   1.0000
  11.250   0.8945   0.09534   0.08880  -0.0223   0.0413   1.0000
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