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S6061 9% (s6061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.72 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6061-il-1000000-n5.txt
Download as CSV file: xf-s6061-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5468   0.08486   0.08329  -0.0162   1.0000   0.0032
  -9.500  -0.5559   0.07877   0.07723  -0.0197   1.0000   0.0031
  -9.250  -0.5653   0.07263   0.07111  -0.0236   1.0000   0.0032
  -9.000  -0.5870   0.06408   0.06262  -0.0311   1.0000   0.0032
  -8.750  -0.6172   0.05298   0.05140  -0.0396   1.0000   0.0030
  -8.500  -0.6689   0.03362   0.03137  -0.0422   1.0000   0.0030
  -8.250  -0.6590   0.02600   0.02303  -0.0445   0.9741   0.0030
  -8.000  -0.6396   0.02291   0.01954  -0.0447   0.9585   0.0031
  -7.750  -0.6219   0.02064   0.01692  -0.0438   0.9436   0.0031
  -7.500  -0.6020   0.01913   0.01515  -0.0429   0.9310   0.0032
  -7.250  -0.5808   0.01780   0.01357  -0.0420   0.9199   0.0033
  -7.000  -0.5568   0.01723   0.01286  -0.0415   0.9100   0.0034
  -6.750  -0.5333   0.01637   0.01182  -0.0409   0.9001   0.0034
  -6.500  -0.5104   0.01506   0.01027  -0.0402   0.8902   0.0035
  -6.250  -0.4874   0.01368   0.00866  -0.0395   0.8810   0.0035
  -6.000  -0.4639   0.01250   0.00725  -0.0388   0.8720   0.0036
  -5.750  -0.4393   0.01161   0.00621  -0.0383   0.8626   0.0037
  -5.500  -0.4140   0.01090   0.00538  -0.0379   0.8537   0.0039
  -5.000  -0.3616   0.00999   0.00429  -0.0373   0.8355   0.0043
  -4.750  -0.3349   0.00964   0.00386  -0.0371   0.8268   0.0047
  -4.500  -0.3080   0.00933   0.00345  -0.0369   0.8174   0.0050
  -4.250  -0.2809   0.00904   0.00310  -0.0367   0.8081   0.0054
  -4.000  -0.2537   0.00880   0.00278  -0.0366   0.7989   0.0057
  -3.750  -0.2263   0.00860   0.00251  -0.0365   0.7891   0.0060
  -3.500  -0.1989   0.00836   0.00220  -0.0364   0.7794   0.0069
  -3.250  -0.1714   0.00816   0.00193  -0.0363   0.7697   0.0086
  -3.000  -0.1438   0.00800   0.00172  -0.0362   0.7594   0.0117
  -2.750  -0.1165   0.00774   0.00152  -0.0361   0.7485   0.0311
  -2.500  -0.0892   0.00752   0.00137  -0.0360   0.7371   0.0581
  -2.250  -0.0619   0.00730   0.00122  -0.0360   0.7249   0.0922
  -2.000  -0.0348   0.00702   0.00110  -0.0360   0.7123   0.1471
  -1.750  -0.0080   0.00670   0.00099  -0.0360   0.6995   0.2228
  -1.500   0.0193   0.00652   0.00090  -0.0360   0.6867   0.2703
  -1.250   0.0464   0.00627   0.00082  -0.0360   0.6738   0.3417
  -1.000   0.0737   0.00611   0.00077  -0.0360   0.6606   0.3944
  -0.750   0.1009   0.00591   0.00072  -0.0360   0.6472   0.4603
  -0.500   0.1280   0.00573   0.00069  -0.0359   0.6332   0.5277
  -0.250   0.1550   0.00557   0.00068  -0.0359   0.6185   0.5936
   0.000   0.1822   0.00546   0.00068  -0.0358   0.6038   0.6475
   0.250   0.2094   0.00539   0.00069  -0.0356   0.5896   0.6923
   0.500   0.2367   0.00536   0.00072  -0.0355   0.5753   0.7292
   0.750   0.2639   0.00535   0.00075  -0.0353   0.5604   0.7607
   1.000   0.2912   0.00537   0.00079  -0.0352   0.5448   0.7877
   1.250   0.3183   0.00540   0.00083  -0.0350   0.5276   0.8109
   1.500   0.3451   0.00546   0.00089  -0.0347   0.5079   0.8330
   1.750   0.3718   0.00552   0.00095  -0.0345   0.4881   0.8550
   2.000   0.3981   0.00560   0.00102  -0.0341   0.4674   0.8758
   2.250   0.4241   0.00569   0.00109  -0.0337   0.4456   0.8965
   2.500   0.4496   0.00581   0.00118  -0.0331   0.4223   0.9165
   3.000   0.5020   0.00616   0.00139  -0.0324   0.3607   0.9580
   3.250   0.5328   0.00652   0.00155  -0.0333   0.3084   0.9748
   3.500   0.5650   0.00697   0.00173  -0.0346   0.2495   0.9878
   3.750   0.5974   0.00731   0.00191  -0.0359   0.2119   0.9997
   4.000   0.6225   0.00768   0.00211  -0.0356   0.1738   1.0000
   4.250   0.6472   0.00810   0.00235  -0.0353   0.1342   1.0000
   4.500   0.6726   0.00845   0.00257  -0.0350   0.1064   1.0000
   4.750   0.6977   0.00884   0.00283  -0.0347   0.0779   1.0000
   5.000   0.7224   0.00931   0.00314  -0.0343   0.0473   1.0000
   5.250   0.7465   0.00987   0.00354  -0.0339   0.0168   1.0000
   5.500   0.7724   0.01016   0.00381  -0.0337   0.0126   1.0000
   5.750   0.7985   0.01043   0.00409  -0.0334   0.0113   1.0000
   6.000   0.8246   0.01069   0.00438  -0.0332   0.0110   1.0000
   6.250   0.8505   0.01097   0.00469  -0.0330   0.0106   1.0000
   6.500   0.8762   0.01127   0.00503  -0.0327   0.0103   1.0000
   6.750   0.9017   0.01160   0.00542  -0.0324   0.0099   1.0000
   7.000   0.9268   0.01196   0.00582  -0.0321   0.0096   1.0000
   7.250   0.9517   0.01235   0.00626  -0.0318   0.0092   1.0000
   7.500   0.9763   0.01277   0.00672  -0.0314   0.0088   1.0000
   7.750   1.0004   0.01323   0.00722  -0.0309   0.0083   1.0000
   8.000   1.0237   0.01380   0.00785  -0.0304   0.0079   1.0000
   8.250   1.0454   0.01455   0.00870  -0.0296   0.0074   1.0000
   8.500   1.0650   0.01553   0.00980  -0.0285   0.0071   1.0000
   8.750   1.0884   0.01597   0.01029  -0.0280   0.0069   1.0000
   9.000   1.1118   0.01638   0.01074  -0.0276   0.0068   1.0000
   9.250   1.1345   0.01687   0.01129  -0.0270   0.0066   1.0000
   9.500   1.1557   0.01750   0.01199  -0.0262   0.0064   1.0000
   9.750   1.1770   0.01807   0.01263  -0.0255   0.0061   1.0000
  10.000   1.1976   0.01869   0.01333  -0.0247   0.0058   1.0000
  10.250   1.2191   0.01917   0.01385  -0.0240   0.0054   1.0000
  10.500   1.2401   0.01967   0.01440  -0.0233   0.0051   1.0000
  10.750   1.2603   0.02021   0.01498  -0.0225   0.0049   1.0000
  11.000   1.2803   0.02072   0.01552  -0.0217   0.0046   1.0000
  11.250   1.2966   0.02153   0.01640  -0.0204   0.0044   1.0000
  11.500   1.3069   0.02277   0.01775  -0.0184   0.0042   1.0000
  11.750   1.3227   0.02336   0.01842  -0.0170   0.0041   1.0000
  12.000   1.3316   0.02425   0.01943  -0.0146   0.0040   1.0000
  12.250   1.3422   0.02503   0.02028  -0.0127   0.0039   1.0000
  12.500   1.3517   0.02592   0.02127  -0.0108   0.0037   1.0000
  12.750   1.3612   0.02687   0.02229  -0.0091   0.0035   1.0000
  13.000   1.3670   0.02815   0.02368  -0.0073   0.0034   1.0000
  13.250   1.3761   0.02924   0.02484  -0.0060   0.0032   1.0000
  13.500   1.3869   0.03025   0.02591  -0.0050   0.0030   1.0000
  13.750   1.3935   0.03167   0.02740  -0.0039   0.0029   1.0000
  14.000   1.4059   0.03266   0.02841  -0.0033   0.0027   1.0000
  14.250   1.4085   0.03460   0.03045  -0.0024   0.0026   1.0000
  14.500   1.4126   0.03651   0.03242  -0.0019   0.0024   1.0000
  14.750   1.4095   0.03930   0.03535  -0.0015   0.0024   1.0000
  15.000   1.4059   0.04233   0.03851  -0.0016   0.0023   1.0000
  15.250   1.4036   0.04542   0.04173  -0.0020   0.0023   1.0000
  15.500   1.3992   0.04896   0.04540  -0.0029   0.0022   1.0000
  15.750   1.3947   0.05270   0.04927  -0.0041   0.0021   1.0000
  16.000   1.3822   0.05786   0.05458  -0.0061   0.0021   1.0000
  16.250   1.3739   0.06265   0.05950  -0.0083   0.0021   1.0000
  16.500   1.3589   0.06886   0.06586  -0.0114   0.0020   1.0000
  16.750   1.3405   0.07607   0.07323  -0.0153   0.0020   1.0000
  17.000   1.3149   0.08512   0.08245  -0.0203   0.0020   1.0000
  17.250   1.2975   0.09291   0.09037  -0.0248   0.0020   1.0000
  17.500   1.2729   0.10253   0.10014  -0.0303   0.0020   1.0000
  17.750   1.2373   0.11490   0.11268  -0.0374   0.0021   1.0000
  18.000   1.2121   0.12535   0.12325  -0.0435   0.0021   1.0000
  18.250   1.1772   0.13843   0.13647  -0.0511   0.0022   1.0000
  18.500   1.1415   0.15242   0.15059  -0.0593   0.0023   1.0000
  18.750   1.1172   0.16396   0.16224  -0.0661   0.0023   1.0000
  19.000   1.0912   0.17663   0.17502  -0.0736   0.0024   1.0000
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