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SG6051 (sg6051-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 100,000
Max Cl/Cd: 58.14 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6051-il-100000.txt
Download as CSV file: xf-sg6051-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6051                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3919   0.09871   0.09409  -0.0440   1.0000   0.1046
  -8.750  -0.4177   0.09703   0.09258  -0.0439   1.0000   0.1066
  -8.500  -0.4484   0.09621   0.09190  -0.0408   1.0000   0.1070
  -8.250  -0.4786   0.09529   0.09111  -0.0374   1.0000   0.1071
  -8.000  -0.5091   0.09318   0.08907  -0.0376   1.0000   0.1075
  -7.750  -0.5411   0.09028   0.08613  -0.0396   1.0000   0.1080
  -7.500  -0.5263   0.08667   0.08267  -0.0336   1.0000   0.1102
  -7.250  -0.5233   0.08484   0.08088  -0.0295   1.0000   0.1129
  -7.000  -0.5309   0.08210   0.07815  -0.0287   1.0000   0.1160
  -6.750  -0.5630   0.07685   0.07247  -0.0378   1.0000   0.1230
  -6.500  -0.5507   0.07329   0.06921  -0.0331   1.0000   0.1253
  -6.250  -0.5414   0.07111   0.06703  -0.0314   0.9992   0.1324
  -6.000  -0.5196   0.06629   0.06208  -0.0362   0.9948   0.1470
  -5.750  -0.4897   0.04799   0.04229  -0.0488   0.9904   0.0831
  -5.500  -0.4571   0.04038   0.03373  -0.0515   0.9872   0.0712
  -5.250  -0.4199   0.03679   0.02936  -0.0542   0.9841   0.0770
  -5.000  -0.3894   0.03386   0.02598  -0.0557   0.9800   0.0840
  -4.750  -0.3536   0.03207   0.02362  -0.0575   0.9759   0.0921
  -4.500  -0.3149   0.02990   0.02113  -0.0601   0.9729   0.0986
  -4.250  -0.2809   0.02878   0.01967  -0.0615   0.9686   0.1057
  -4.000  -0.2475   0.02746   0.01820  -0.0629   0.9642   0.1121
  -3.750  -0.2092   0.02663   0.01719  -0.0651   0.9603   0.1208
  -3.500  -0.1693   0.02566   0.01627  -0.0678   0.9573   0.1315
  -3.250  -0.1430   0.02503   0.01568  -0.0679   0.9513   0.1438
  -3.000  -0.1068   0.02433   0.01506  -0.0699   0.9471   0.1652
  -2.750  -0.0660   0.02283   0.01437  -0.0732   0.9444   0.2696
  -2.500  -0.0406   0.02170   0.01466  -0.0728   0.9400   0.5985
  -2.250  -0.0185   0.02147   0.01489  -0.0710   0.9343   0.7306
  -2.000   0.0116   0.02138   0.01514  -0.0695   0.9302   0.9103
  -1.750   0.0546   0.02161   0.01510  -0.0734   0.9241   1.0000
  -1.500   0.0864   0.02188   0.01512  -0.0749   0.9178   1.0000
  -1.250   0.1299   0.02211   0.01508  -0.0786   0.9140   1.0000
  -1.000   0.1474   0.02255   0.01535  -0.0774   0.9054   1.0000
  -0.750   0.1868   0.02278   0.01540  -0.0801   0.9006   1.0000
  -0.500   0.2107   0.02322   0.01570  -0.0800   0.8932   1.0000
  -0.250   0.2441   0.02351   0.01585  -0.0816   0.8871   1.0000
   0.000   0.2895   0.02365   0.01587  -0.0852   0.8837   1.0000
   0.250   0.3016   0.02427   0.01641  -0.0830   0.8736   1.0000
   0.500   0.3446   0.02440   0.01645  -0.0861   0.8697   1.0000
   0.750   0.3593   0.02505   0.01704  -0.0844   0.8602   1.0000
   1.000   0.3996   0.02518   0.01712  -0.0869   0.8556   1.0000
   1.250   0.4180   0.02580   0.01770  -0.0858   0.8466   1.0000
   1.500   0.4558   0.02594   0.01782  -0.0878   0.8413   1.0000
   1.750   0.4782   0.02647   0.01834  -0.0873   0.8329   1.0000
   2.000   0.5136   0.02662   0.01848  -0.0888   0.8268   1.0000
   2.250   0.5585   0.02640   0.01826  -0.0915   0.8235   1.0000
   2.500   0.5720   0.02714   0.01902  -0.0896   0.8118   1.0000
   2.750   0.5962   0.02757   0.01948  -0.0891   0.8031   1.0000
   3.000   0.6315   0.02749   0.01945  -0.0902   0.7967   1.0000
   3.250   0.6538   0.02794   0.01993  -0.0894   0.7869   1.0000
   3.500   0.6924   0.02757   0.01964  -0.0906   0.7813   1.0000
   3.750   0.7145   0.02793   0.02006  -0.0897   0.7706   1.0000
   4.000   0.7563   0.02719   0.01940  -0.0909   0.7657   1.0000
   4.250   0.7783   0.02744   0.01975  -0.0898   0.7542   1.0000
   4.500   0.8229   0.02630   0.01871  -0.0910   0.7500   1.0000
   4.750   0.8459   0.02633   0.01884  -0.0898   0.7377   1.0000
   5.000   0.8730   0.02605   0.01868  -0.0889   0.7263   1.0000
   5.250   0.9168   0.02455   0.01729  -0.0895   0.7205   1.0000
   5.500   0.9440   0.02406   0.01693  -0.0883   0.7073   1.0000
   5.750   0.9733   0.02335   0.01634  -0.0873   0.6937   1.0000
   6.000   1.0039   0.02248   0.01559  -0.0863   0.6792   1.0000
   6.250   1.0357   0.02146   0.01466  -0.0853   0.6629   1.0000
   6.500   1.0609   0.02087   0.01420  -0.0837   0.6416   1.0000
   6.750   1.0893   0.02009   0.01347  -0.0823   0.6181   1.0000
   7.000   1.1120   0.01972   0.01316  -0.0804   0.5880   1.0000
   7.250   1.1308   0.01962   0.01313  -0.0780   0.5486   1.0000
   7.500   1.1477   0.01974   0.01314  -0.0753   0.4982   1.0000
   7.750   1.1587   0.02033   0.01346  -0.0720   0.4315   1.0000
   8.000   1.1618   0.02155   0.01420  -0.0678   0.3536   1.0000
   8.250   1.1579   0.02331   0.01542  -0.0629   0.2778   1.0000
   8.500   1.1508   0.02529   0.01691  -0.0578   0.2178   1.0000
   8.750   1.1442   0.02735   0.01857  -0.0530   0.1770   1.0000
   9.000   1.1434   0.02939   0.02035  -0.0492   0.1472   1.0000
   9.250   1.1476   0.03128   0.02206  -0.0463   0.1265   1.0000
   9.500   1.1572   0.03314   0.02376  -0.0440   0.1116   1.0000
   9.750   1.1713   0.03485   0.02541  -0.0423   0.0991   1.0000
  10.000   1.1898   0.03658   0.02718  -0.0411   0.0888   1.0000
  10.250   1.2113   0.03849   0.02911  -0.0403   0.0796   1.0000
  10.500   1.2402   0.04079   0.03132  -0.0407   0.0710   1.0000
  10.750   1.2570   0.04271   0.03355  -0.0392   0.0654   1.0000
  11.000   1.2889   0.04585   0.03667  -0.0404   0.0591   1.0000
  11.250   1.2993   0.04826   0.03951  -0.0381   0.0562   1.0000
  11.500   1.3131   0.05126   0.04284  -0.0365   0.0538   1.0000
  11.750   1.3239   0.05408   0.04587  -0.0349   0.0517   1.0000
  12.000   1.3431   0.05969   0.05158  -0.0355   0.0490   1.0000
  12.250   1.3284   0.06187   0.05417  -0.0309   0.0485   1.0000
  12.500   1.3139   0.06477   0.05744  -0.0271   0.0480   1.0000
  12.750   1.2990   0.06826   0.06128  -0.0240   0.0478   1.0000
  13.000   1.2829   0.07224   0.06557  -0.0215   0.0477   1.0000
  13.250   1.2650   0.07655   0.07018  -0.0195   0.0478   1.0000
  13.500   1.2452   0.08121   0.07511  -0.0181   0.0479   1.0000
  13.750   1.2244   0.08626   0.08041  -0.0175   0.0481   1.0000
  14.000   1.2028   0.09174   0.08610  -0.0175   0.0483   1.0000
  14.250   1.1817   0.09768   0.09223  -0.0182   0.0486   1.0000
  14.500   1.1636   0.10425   0.09895  -0.0194   0.0490   1.0000
  14.750   1.1365   0.10990   0.10484  -0.0221   0.0495   1.0000
  15.000   1.0205   0.13699   0.13242  -0.0420   0.0579   1.0000
  15.250   1.0063   0.14643   0.14186  -0.0469   0.0592   1.0000
  15.500   1.0020   0.15358   0.14900  -0.0496   0.0599   1.0000
  15.750   0.6926   0.16983   0.16533  -0.0441   0.1370   1.0000
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