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SA7026 (sa7026-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 500,000
Max Cl/Cd: 121.05 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7026-il-500000.txt
Download as CSV file: xf-sa7026-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3358   0.10221   0.10003  -0.0384   1.0000   0.0122
  -9.250  -0.3427   0.10125   0.09912  -0.0349   1.0000   0.0125
  -9.000  -0.3394   0.09868   0.09657  -0.0355   0.9991   0.0129
  -8.750  -0.3249   0.09471   0.09260  -0.0395   0.9969   0.0134
  -8.500  -0.3101   0.09061   0.08850  -0.0441   0.9943   0.0140
  -8.250  -0.2966   0.08633   0.08421  -0.0488   0.9907   0.0151
  -8.000  -0.2809   0.08171   0.07960  -0.0546   0.9872   0.0157
  -7.750  -0.1777   0.05620   0.05418  -0.0727   0.9758   0.0184
  -7.500  -0.1651   0.05226   0.05024  -0.0762   0.9724   0.0190
  -7.250  -0.1575   0.04847   0.04645  -0.0795   0.9654   0.0195
  -7.000  -0.1529   0.04439   0.04236  -0.0836   0.9576   0.0198
  -6.750  -0.1510   0.04031   0.03825  -0.0875   0.9475   0.0202
  -6.500  -0.1465   0.03578   0.03367  -0.0918   0.9390   0.0206
  -6.250  -0.1399   0.03110   0.02889  -0.0954   0.9313   0.0212
  -6.000  -0.1301   0.02644   0.02408  -0.0984   0.9240   0.0221
  -5.750  -0.1161   0.02193   0.01934  -0.1006   0.9180   0.0238
  -5.500  -0.0942   0.01991   0.01696  -0.1011   0.9121   0.0254
  -5.250  -0.0873   0.01317   0.00975  -0.1027   0.9056   0.0265
  -5.000  -0.0693   0.01100   0.00749  -0.1026   0.9013   0.0278
  -4.750  -0.0479   0.00956   0.00592  -0.1027   0.8954   0.0294
  -4.500  -0.0252   0.00813   0.00424  -0.1025   0.8907   0.0321
  -4.250   0.0028   0.00854   0.00435  -0.1013   0.8858   0.0362
  -4.000   0.0340   0.01566   0.01023  -0.1068   0.8938   0.0177
  -3.750   0.0597   0.01393   0.00831  -0.1061   0.8896   0.0168
  -3.500   0.0856   0.01275   0.00696  -0.1055   0.8847   0.0169
  -3.250   0.1121   0.01217   0.00627  -0.1051   0.8794   0.0173
  -3.000   0.1374   0.01090   0.00486  -0.1044   0.8750   0.0183
  -2.750   0.1636   0.01030   0.00420  -0.1040   0.8693   0.0183
  -2.500   0.1902   0.00977   0.00358  -0.1036   0.8636   0.0185
  -2.250   0.2173   0.00935   0.00305  -0.1032   0.8585   0.0196
  -2.000   0.2444   0.00906   0.00270  -0.1029   0.8521   0.0224
  -1.750   0.2714   0.00852   0.00234  -0.1026   0.8471   0.0896
  -1.500   0.2972   0.00791   0.00222  -0.1025   0.8406   0.2395
  -1.250   0.3226   0.00729   0.00216  -0.1024   0.8347   0.4252
  -1.000   0.3475   0.00684   0.00214  -0.1019   0.8284   0.5774
  -0.750   0.3696   0.00630   0.00215  -0.1005   0.8215   0.7546
  -0.500   0.4127   0.00576   0.00204  -0.1031   0.8156   0.9930
  -0.250   0.4419   0.00577   0.00195  -0.1033   0.8076   1.0000
   0.000   0.4684   0.00579   0.00189  -0.1030   0.7996   1.0000
   0.250   0.4952   0.00582   0.00182  -0.1027   0.7919   1.0000
   0.500   0.5219   0.00585   0.00180  -0.1024   0.7829   1.0000
   0.750   0.5487   0.00590   0.00176  -0.1021   0.7745   1.0000
   1.000   0.5755   0.00594   0.00174  -0.1018   0.7650   1.0000
   1.250   0.6022   0.00599   0.00174  -0.1015   0.7544   1.0000
   1.500   0.6289   0.00605   0.00174  -0.1012   0.7432   1.0000
   1.750   0.6555   0.00612   0.00176  -0.1009   0.7314   1.0000
   2.000   0.6820   0.00620   0.00178  -0.1006   0.7191   1.0000
   2.250   0.7084   0.00630   0.00182  -0.1002   0.7062   1.0000
   2.500   0.7348   0.00639   0.00187  -0.0999   0.6925   1.0000
   2.750   0.7610   0.00650   0.00193  -0.0996   0.6777   1.0000
   3.000   0.7870   0.00662   0.00202  -0.0992   0.6617   1.0000
   3.250   0.8128   0.00677   0.00211  -0.0988   0.6443   1.0000
   3.500   0.8380   0.00695   0.00221  -0.0982   0.6250   1.0000
   3.750   0.8631   0.00713   0.00233  -0.0977   0.6028   1.0000
   4.000   0.8878   0.00735   0.00249  -0.0971   0.5805   1.0000
   4.250   0.9124   0.00758   0.00265  -0.0965   0.5571   1.0000
   4.500   0.9367   0.00783   0.00283  -0.0959   0.5333   1.0000
   4.750   0.9606   0.00811   0.00304  -0.0952   0.5091   1.0000
   5.000   0.9839   0.00843   0.00328  -0.0945   0.4819   1.0000
   5.250   1.0066   0.00879   0.00353  -0.0936   0.4504   1.0000
   5.500   1.0290   0.00918   0.00381  -0.0927   0.4190   1.0000
   5.750   1.0503   0.00964   0.00412  -0.0917   0.3817   1.0000
   6.000   1.0705   0.01019   0.00447  -0.0905   0.3378   1.0000
   6.500   1.1094   0.01144   0.00531  -0.0880   0.2497   1.0000
   6.750   1.1293   0.01204   0.00574  -0.0869   0.2138   1.0000
   7.000   1.1475   0.01276   0.00626  -0.0855   0.1718   1.0000
   7.250   1.1632   0.01370   0.00689  -0.0838   0.1210   1.0000
   7.500   1.1770   0.01477   0.00766  -0.0818   0.0717   1.0000
   7.750   1.1889   0.01597   0.00856  -0.0795   0.0293   1.0000
   8.000   1.2016   0.01710   0.00959  -0.0771   0.0115   1.0000
   8.250   1.2167   0.01798   0.01056  -0.0750   0.0093   1.0000
   8.500   1.2313   0.01872   0.01141  -0.0729   0.0089   1.0000
   8.750   1.2445   0.01950   0.01229  -0.0706   0.0085   1.0000
   9.000   1.2557   0.02041   0.01330  -0.0680   0.0082   1.0000
   9.250   1.2654   0.02143   0.01444  -0.0653   0.0078   1.0000
   9.500   1.2741   0.02253   0.01567  -0.0626   0.0077   1.0000
   9.750   1.2812   0.02379   0.01704  -0.0599   0.0075   1.0000
  10.000   1.2870   0.02519   0.01856  -0.0571   0.0074   1.0000
  10.250   1.2922   0.02673   0.02022  -0.0544   0.0074   1.0000
  10.500   1.2976   0.02837   0.02199  -0.0520   0.0074   1.0000
  10.750   1.3031   0.03013   0.02388  -0.0496   0.0074   1.0000
  11.000   1.3095   0.03190   0.02577  -0.0475   0.0073   1.0000
  11.250   1.3171   0.03345   0.02742  -0.0458   0.0070   1.0000
  11.500   1.3233   0.03528   0.02937  -0.0441   0.0068   1.0000
  11.750   1.3287   0.03714   0.03132  -0.0425   0.0066   1.0000
  12.000   1.3331   0.03958   0.03395  -0.0407   0.0066   1.0000
  12.250   1.3366   0.04205   0.03658  -0.0392   0.0066   1.0000
  12.500   1.3386   0.04481   0.03956  -0.0376   0.0066   1.0000
  12.750   1.3383   0.04794   0.04293  -0.0362   0.0067   1.0000
  13.000   1.3354   0.05127   0.04647  -0.0350   0.0067   1.0000
  13.250   1.3308   0.05470   0.05009  -0.0342   0.0066   1.0000
  13.500   1.3187   0.05974   0.05545  -0.0333   0.0069   1.0000
  13.750   1.2945   0.06660   0.06272  -0.0333   0.0074   1.0000
  14.000   1.2756   0.07261   0.06900  -0.0343   0.0076   1.0000
  14.250   1.2576   0.07877   0.07537  -0.0361   0.0075   1.0000
  14.500   1.2356   0.08614   0.08297  -0.0389   0.0078   1.0000
  14.750   1.2172   0.09337   0.09040  -0.0423   0.0078   1.0000
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