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SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7043 (9.1%) (sd7043-il)
Reynolds number: 200,000
Max Cl/Cd: 75.95 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7043-il-200000-n5.txt
Download as CSV file: xf-sd7043-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7043 (9.1%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3605   0.08399   0.08050  -0.0390   1.0000   0.0146
  -8.250  -0.3663   0.08124   0.07782  -0.0385   1.0000   0.0146
  -8.000  -0.3807   0.07881   0.07549  -0.0368   1.0000   0.0146
  -7.750  -0.3793   0.07584   0.07257  -0.0385   0.9957   0.0144
  -7.500  -0.3636   0.07005   0.06676  -0.0466   0.9870   0.0143
  -7.250  -0.3448   0.06017   0.05686  -0.0618   0.9778   0.0144
  -7.000  -0.3216   0.04479   0.04111  -0.0814   0.9691   0.0144
  -6.750  -0.3007   0.03700   0.03283  -0.0893   0.9612   0.0151
  -6.500  -0.2714   0.03387   0.02942  -0.0933   0.9575   0.0157
  -6.250  -0.2500   0.02872   0.02364  -0.0958   0.9495   0.0160
  -6.000  -0.2211   0.02506   0.01938  -0.0980   0.9450   0.0165
  -5.750  -0.1935   0.02242   0.01622  -0.0990   0.9399   0.0173
  -5.500  -0.1661   0.02039   0.01371  -0.0993   0.9342   0.0182
  -5.250  -0.1362   0.01900   0.01205  -0.1000   0.9300   0.0197
  -5.000  -0.1086   0.01821   0.01115  -0.1002   0.9247   0.0214
  -4.750  -0.0812   0.01714   0.00988  -0.1001   0.9189   0.0228
  -4.500  -0.0518   0.01622   0.00876  -0.1003   0.9144   0.0241
  -4.250  -0.0255   0.01540   0.00795  -0.1001   0.9085   0.0263
  -4.000   0.0020   0.01483   0.00731  -0.1000   0.9026   0.0288
  -3.750   0.0308   0.01422   0.00658  -0.1000   0.8981   0.0306
  -3.500   0.0567   0.01366   0.00603  -0.0997   0.8909   0.0338
  -3.250   0.0847   0.01323   0.00553  -0.0996   0.8852   0.0370
  -3.000   0.1123   0.01281   0.00504  -0.0994   0.8791   0.0404
  -2.750   0.1396   0.01246   0.00467  -0.0992   0.8721   0.0477
  -2.500   0.1678   0.01204   0.00427  -0.0990   0.8664   0.0643
  -2.250   0.1946   0.01164   0.00402  -0.0988   0.8585   0.1054
  -2.000   0.2224   0.01121   0.00380  -0.0988   0.8525   0.1719
  -1.750   0.2489   0.01080   0.00369  -0.0987   0.8439   0.2599
  -1.500   0.2760   0.01031   0.00359  -0.0986   0.8373   0.3837
  -1.250   0.3018   0.00995   0.00357  -0.0982   0.8280   0.4899
  -1.000   0.3281   0.00969   0.00351  -0.0975   0.8202   0.5713
  -0.750   0.3531   0.00946   0.00349  -0.0966   0.8107   0.6510
  -0.500   0.3775   0.00926   0.00347  -0.0954   0.8011   0.7211
  -0.250   0.4009   0.00908   0.00340  -0.0938   0.7918   0.7871
   0.000   0.4234   0.00892   0.00333  -0.0920   0.7803   0.8551
   0.250   0.4542   0.00871   0.00317  -0.0920   0.7687   0.9484
   0.500   0.4851   0.00871   0.00306  -0.0925   0.7561   1.0000
   0.750   0.5128   0.00877   0.00300  -0.0922   0.7428   1.0000
   1.000   0.5404   0.00883   0.00295  -0.0920   0.7283   1.0000
   1.250   0.5678   0.00891   0.00293  -0.0917   0.7123   1.0000
   1.500   0.5950   0.00900   0.00292  -0.0914   0.6949   1.0000
   1.750   0.6220   0.00911   0.00291  -0.0910   0.6762   1.0000
   2.000   0.6489   0.00925   0.00293  -0.0906   0.6564   1.0000
   2.250   0.6755   0.00940   0.00298  -0.0902   0.6345   1.0000
   2.500   0.7019   0.00959   0.00304  -0.0898   0.6122   1.0000
   2.750   0.7281   0.00979   0.00313  -0.0893   0.5878   1.0000
   3.000   0.7539   0.01003   0.00324  -0.0888   0.5628   1.0000
   3.250   0.7794   0.01030   0.00339  -0.0883   0.5363   1.0000
   3.500   0.8045   0.01060   0.00355  -0.0877   0.5080   1.0000
   3.750   0.8294   0.01092   0.00374  -0.0872   0.4788   1.0000
   4.000   0.8539   0.01128   0.00397  -0.0866   0.4486   1.0000
   4.250   0.8782   0.01166   0.00421  -0.0860   0.4186   1.0000
   4.500   0.9022   0.01207   0.00449  -0.0853   0.3887   1.0000
   4.750   0.9260   0.01250   0.00478  -0.0847   0.3592   1.0000
   5.000   0.9497   0.01295   0.00513  -0.0841   0.3309   1.0000
   5.250   0.9732   0.01341   0.00547  -0.0835   0.3042   1.0000
   5.500   0.9965   0.01388   0.00585  -0.0828   0.2795   1.0000
   5.750   1.0197   0.01438   0.00626  -0.0822   0.2560   1.0000
   6.000   1.0428   0.01487   0.00667  -0.0815   0.2342   1.0000
   6.250   1.0657   0.01538   0.00711  -0.0808   0.2143   1.0000
   6.750   1.1107   0.01645   0.00808  -0.0794   0.1796   1.0000
   7.000   1.1330   0.01699   0.00858  -0.0787   0.1641   1.0000
   7.250   1.1550   0.01755   0.00911  -0.0779   0.1502   1.0000
   7.500   1.1765   0.01813   0.00967  -0.0771   0.1374   1.0000
   7.750   1.1978   0.01873   0.01027  -0.0762   0.1261   1.0000
   8.000   1.2190   0.01930   0.01087  -0.0754   0.1160   1.0000
   8.250   1.2395   0.01993   0.01151  -0.0744   0.1068   1.0000
   8.500   1.2589   0.02063   0.01220  -0.0733   0.0982   1.0000
   8.750   1.2788   0.02126   0.01291  -0.0723   0.0906   1.0000
   9.000   1.2970   0.02201   0.01368  -0.0711   0.0842   1.0000
   9.250   1.3153   0.02272   0.01445  -0.0698   0.0778   1.0000
   9.500   1.3316   0.02355   0.01530  -0.0684   0.0725   1.0000
   9.750   1.3481   0.02430   0.01615  -0.0669   0.0677   1.0000
  10.000   1.3608   0.02521   0.01709  -0.0650   0.0636   1.0000
  10.250   1.3740   0.02608   0.01806  -0.0631   0.0601   1.0000
  10.500   1.3870   0.02697   0.01905  -0.0613   0.0566   1.0000
  10.750   1.3976   0.02803   0.02016  -0.0594   0.0538   1.0000
  11.000   1.4061   0.02927   0.02145  -0.0573   0.0513   1.0000
  11.250   1.4177   0.03033   0.02268  -0.0556   0.0489   1.0000
  11.500   1.4278   0.03152   0.02400  -0.0540   0.0466   1.0000
  11.750   1.4358   0.03289   0.02545  -0.0523   0.0445   1.0000
  12.000   1.4406   0.03457   0.02719  -0.0505   0.0428   1.0000
  12.250   1.4475   0.03617   0.02893  -0.0490   0.0413   1.0000
  12.500   1.4550   0.03776   0.03068  -0.0476   0.0396   1.0000
  12.750   1.4610   0.03951   0.03257  -0.0464   0.0381   1.0000
  13.000   1.4658   0.04141   0.03460  -0.0453   0.0366   1.0000
  13.250   1.4682   0.04360   0.03691  -0.0443   0.0354   1.0000
  13.500   1.4675   0.04623   0.03962  -0.0434   0.0343   1.0000
  13.750   1.4689   0.04878   0.04233  -0.0427   0.0333   1.0000
  14.000   1.4709   0.05136   0.04511  -0.0423   0.0322   1.0000
  14.250   1.4713   0.05420   0.04813  -0.0421   0.0312   1.0000
  14.500   1.4703   0.05731   0.05140  -0.0422   0.0302   1.0000
  14.750   1.4679   0.06070   0.05494  -0.0425   0.0294   1.0000
  15.000   1.4643   0.06440   0.05879  -0.0432   0.0286   1.0000
  15.250   1.4592   0.06846   0.06298  -0.0442   0.0280   1.0000
  15.500   1.4521   0.07297   0.06760  -0.0456   0.0273   1.0000
  15.750   1.4441   0.07784   0.07259  -0.0472   0.0267   1.0000
  16.000   1.4368   0.08288   0.07786  -0.0492   0.0262   1.0000
  16.250   1.4279   0.08838   0.08358  -0.0516   0.0256   1.0000
  16.500   1.4178   0.09430   0.08970  -0.0544   0.0250   1.0000
  16.750   1.4067   0.10061   0.09620  -0.0576   0.0245   1.0000
  17.000   1.3945   0.10730   0.10307  -0.0612   0.0240   1.0000
  17.250   1.3817   0.11433   0.11028  -0.0651   0.0236   1.0000
  17.500   1.3683   0.12170   0.11780  -0.0694   0.0232   1.0000
  17.750   1.3545   0.12937   0.12563  -0.0740   0.0229   1.0000
  18.000   1.3400   0.13735   0.13376  -0.0790   0.0226   1.0000
  18.250   1.3250   0.14572   0.14227  -0.0843   0.0223   1.0000
  18.500   1.3087   0.15465   0.15134  -0.0901   0.0221   1.0000
  18.750   1.2823   0.16681   0.16369  -0.0982   0.0221   1.0000
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