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SG6041 (sg6041-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SG6041 (sg6041-il)
Reynolds number: 50,000
Max Cl/Cd: 35.45 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6041-il-50000.txt
Download as CSV file: xf-sg6041-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6041                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4144   0.10972   0.10264  -0.0221   1.0000   0.2413
  -9.000  -0.4361   0.10911   0.10219  -0.0229   1.0000   0.2510
  -8.750  -0.4205   0.10488   0.09798  -0.0213   1.0000   0.2647
  -8.500  -0.4115   0.10128   0.09441  -0.0200   1.0000   0.2776
  -8.250  -0.4078   0.09824   0.09144  -0.0189   1.0000   0.2908
  -8.000  -0.4065   0.09544   0.08871  -0.0175   1.0000   0.3051
  -7.750  -0.4071   0.09288   0.08623  -0.0159   1.0000   0.3217
  -7.500  -0.4179   0.09109   0.08457  -0.0139   1.0000   0.3400
  -7.250  -0.4021   0.08751   0.08102  -0.0114   1.0000   0.3631
  -7.000  -0.4168   0.08630   0.07995  -0.0082   1.0000   0.3857
  -6.750  -0.4150   0.08406   0.07779  -0.0045   1.0000   0.4163
  -6.500  -0.4094   0.08166   0.07546  -0.0010   1.0000   0.4465
  -5.250  -0.5020   0.05150   0.04403  -0.0291   1.0000   0.1452
  -5.000  -0.4861   0.04695   0.03899  -0.0287   1.0000   0.1296
  -4.750  -0.4701   0.04340   0.03513  -0.0277   1.0000   0.1262
  -4.500  -0.4516   0.04004   0.03122  -0.0269   1.0000   0.1229
  -4.250  -0.4300   0.03703   0.02747  -0.0259   1.0000   0.1191
  -4.000  -0.4071   0.03445   0.02431  -0.0247   1.0000   0.1183
  -3.750  -0.3854   0.03224   0.02203  -0.0238   1.0000   0.1247
  -3.500  -0.3607   0.03042   0.01965  -0.0226   1.0000   0.1313
  -3.250  -0.3367   0.02848   0.01767  -0.0217   1.0000   0.1422
  -3.000  -0.3120   0.02687   0.01589  -0.0205   1.0000   0.1588
  -2.750  -0.2880   0.02535   0.01448  -0.0192   1.0000   0.1859
  -2.500  -0.2642   0.02384   0.01317  -0.0179   1.0000   0.2322
  -2.250  -0.1425   0.02093   0.01297  -0.0247   1.0000   1.0000
  -2.000  -0.1436   0.02063   0.01246  -0.0210   1.0000   1.0000
  -1.750  -0.1425   0.02038   0.01199  -0.0177   1.0000   1.0000
  -1.500  -0.1379   0.02022   0.01159  -0.0148   1.0000   1.0000
  -1.250  -0.1286   0.02016   0.01128  -0.0126   1.0000   1.0000
  -1.000  -0.1155   0.02021   0.01108  -0.0111   1.0000   1.0000
  -0.750  -0.1001   0.02033   0.01095  -0.0099   1.0000   1.0000
  -0.500  -0.0834   0.02052   0.01092  -0.0089   1.0000   1.0000
  -0.250  -0.0658   0.02077   0.01096  -0.0081   1.0000   1.0000
   0.000  -0.0478   0.02107   0.01108  -0.0074   1.0000   1.0000
   0.250  -0.0296   0.02141   0.01125  -0.0068   1.0000   1.0000
   0.500  -0.0112   0.02181   0.01150  -0.0063   1.0000   1.0000
   0.750   0.0071   0.02225   0.01182  -0.0058   1.0000   1.0000
   1.000   0.0253   0.02274   0.01220  -0.0054   1.0000   1.0000
   1.250   0.0433   0.02329   0.01265  -0.0050   1.0000   1.0000
   1.500   0.0611   0.02389   0.01318  -0.0047   1.0000   1.0000
   1.750   0.0785   0.02455   0.01378  -0.0044   1.0000   1.0000
   2.000   0.0955   0.02527   0.01445  -0.0043   1.0000   1.0000
   2.250   0.1122   0.02606   0.01521  -0.0041   1.0000   1.0000
   2.500   0.1725   0.02792   0.01707  -0.0122   0.9781   1.0000
   2.750   0.2304   0.02953   0.01871  -0.0193   0.9560   1.0000
   3.000   0.2810   0.03067   0.01992  -0.0247   0.9319   1.0000
   3.250   0.3300   0.03163   0.02097  -0.0294   0.9072   1.0000
   3.500   0.3853   0.03238   0.02185  -0.0346   0.8825   1.0000
   3.750   0.4366   0.03275   0.02237  -0.0385   0.8561   1.0000
   4.000   0.4842   0.03282   0.02264  -0.0412   0.8284   1.0000
   4.250   0.5353   0.03245   0.02247  -0.0438   0.8001   1.0000
   4.500   0.5921   0.03142   0.02173  -0.0462   0.7713   1.0000
   4.750   0.6557   0.02954   0.02016  -0.0484   0.7417   1.0000
   5.000   0.7199   0.02701   0.01795  -0.0496   0.7088   1.0000
   5.250   0.7687   0.02503   0.01612  -0.0487   0.6652   1.0000
   5.500   0.8064   0.02387   0.01491  -0.0467   0.6090   1.0000
   5.750   0.8373   0.02362   0.01437  -0.0445   0.5441   1.0000
   6.000   0.8582   0.02431   0.01469  -0.0418   0.4809   1.0000
   6.250   0.8795   0.02534   0.01529  -0.0397   0.4257   1.0000
   6.500   0.8993   0.02663   0.01633  -0.0378   0.3796   1.0000
   6.750   0.9196   0.02802   0.01757  -0.0362   0.3411   1.0000
   7.000   0.9420   0.02953   0.01889  -0.0350   0.3092   1.0000
   7.250   0.9632   0.03116   0.02052  -0.0338   0.2828   1.0000
   7.500   0.9867   0.03296   0.02227  -0.0330   0.2609   1.0000
   7.750   1.0057   0.03475   0.02422  -0.0316   0.2414   1.0000
   8.000   1.0267   0.03692   0.02654  -0.0305   0.2264   1.0000
   8.250   1.0449   0.03903   0.02882  -0.0291   0.2120   1.0000
   8.500   1.0625   0.04143   0.03142  -0.0277   0.2003   1.0000
   8.750   1.0823   0.04390   0.03397  -0.0267   0.1893   1.0000
   9.000   1.0903   0.04646   0.03697  -0.0243   0.1798   1.0000
   9.250   1.1008   0.04968   0.04049  -0.0224   0.1733   1.0000
   9.500   1.1007   0.05304   0.04432  -0.0196   0.1676   1.0000
   9.750   1.1140   0.05600   0.04735  -0.0182   0.1600   1.0000
  10.000   1.1014   0.06010   0.05197  -0.0149   0.1578   1.0000
  10.250   1.0856   0.06459   0.05685  -0.0119   0.1570   1.0000
  10.500   1.0641   0.06931   0.06186  -0.0092   0.1573   1.0000
  10.750   1.0366   0.07407   0.06681  -0.0066   0.1582   1.0000
  11.000   1.0088   0.07928   0.07213  -0.0052   0.1595   1.0000
  11.250   0.9853   0.08521   0.07813  -0.0054   0.1608   1.0000
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