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SG6042 (sg6042-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 100,000
Max Cl/Cd: 62.91 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6042-il-100000.txt
Download as CSV file: xf-sg6042-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3849   0.10623   0.10162  -0.0324   1.0000   0.0818
  -8.000  -0.4079   0.10564   0.10114  -0.0312   1.0000   0.0822
  -7.750  -0.4303   0.10485   0.10046  -0.0295   1.0000   0.0824
  -7.500  -0.4484   0.10308   0.09876  -0.0309   1.0000   0.0826
  -7.250  -0.4637   0.10038   0.09608  -0.0349   1.0000   0.0828
  -7.000  -0.4315   0.09527   0.09102  -0.0221   1.0000   0.0860
  -6.750  -0.4358   0.09313   0.08893  -0.0201   1.0000   0.0880
  -6.500  -0.4428   0.09083   0.08669  -0.0193   1.0000   0.0907
  -6.250  -0.4500   0.08821   0.08412  -0.0203   1.0000   0.0929
  -6.000  -0.4589   0.08419   0.08002  -0.0307   1.0000   0.0967
  -5.750  -0.4593   0.07955   0.07541  -0.0311   1.0000   0.0987
  -5.500  -0.4551   0.07762   0.07357  -0.0259   1.0000   0.1015
  -5.250  -0.4500   0.07491   0.07086  -0.0259   1.0000   0.1063
  -5.000  -0.4384   0.06931   0.06502  -0.0349   1.0000   0.1139
  -4.750  -0.4322   0.06702   0.06283  -0.0316   1.0000   0.1170
  -4.500  -0.4118   0.06259   0.05805  -0.0387   1.0000   0.1290
  -4.250  -0.4030   0.05988   0.05548  -0.0362   1.0000   0.1321
  -4.000  -0.3819   0.05625   0.05162  -0.0400   1.0000   0.1456
  -3.750  -0.3672   0.05386   0.04926  -0.0391   0.9999   0.1524
  -3.500  -0.3247   0.05004   0.04516  -0.0462   0.9947   0.1775
  -3.250  -0.2912   0.04749   0.04252  -0.0495   0.9889   0.2087
  -3.000  -0.2034   0.03452   0.02728  -0.0603   0.9879   0.0783
  -2.750  -0.1562   0.03106   0.02292  -0.0635   0.9846   0.0717
  -2.500  -0.1206   0.02951   0.02109  -0.0652   0.9786   0.0742
  -2.250  -0.0789   0.02838   0.01961  -0.0677   0.9739   0.0788
  -2.000  -0.0440   0.02737   0.01824  -0.0687   0.9677   0.0824
  -1.750  -0.0063   0.02632   0.01724  -0.0707   0.9625   0.0940
  -1.500   0.0295   0.02543   0.01639  -0.0721   0.9569   0.1138
  -1.250   0.0636   0.02464   0.01589  -0.0737   0.9505   0.1619
  -1.000   0.0998   0.02245   0.01590  -0.0757   0.9473   0.6084
  -0.750   0.1189   0.02168   0.01580  -0.0721   0.9383   1.0000
  -0.500   0.1643   0.02218   0.01590  -0.0757   0.9326   1.0000
  -0.250   0.1926   0.02243   0.01591  -0.0763   0.9226   1.0000
   0.000   0.2320   0.02282   0.01606  -0.0787   0.9156   1.0000
   0.250   0.2657   0.02311   0.01617  -0.0802   0.9065   1.0000
   0.500   0.2991   0.02343   0.01634  -0.0816   0.8979   1.0000
   0.750   0.3392   0.02367   0.01643  -0.0840   0.8903   1.0000
   1.000   0.3686   0.02395   0.01661  -0.0845   0.8801   1.0000
   1.250   0.4150   0.02403   0.01659  -0.0878   0.8739   1.0000
   1.500   0.4422   0.02424   0.01674  -0.0878   0.8623   1.0000
   1.750   0.4784   0.02433   0.01677  -0.0892   0.8532   1.0000
   2.000   0.5200   0.02422   0.01663  -0.0914   0.8450   1.0000
   2.250   0.5503   0.02430   0.01669  -0.0917   0.8337   1.0000
   2.500   0.6014   0.02380   0.01618  -0.0950   0.8283   1.0000
   2.750   0.6307   0.02374   0.01613  -0.0949   0.8160   1.0000
   3.000   0.6900   0.02268   0.01512  -0.0992   0.8122   1.0000
   3.250   0.7208   0.02239   0.01487  -0.0990   0.7994   1.0000
   3.500   0.7564   0.02192   0.01445  -0.0995   0.7875   1.0000
   3.750   0.8129   0.02061   0.01320  -0.1029   0.7814   1.0000
   4.000   0.8480   0.01998   0.01265  -0.1030   0.7679   1.0000
   4.250   0.8832   0.01932   0.01205  -0.1031   0.7535   1.0000
   4.500   0.9201   0.01859   0.01137  -0.1034   0.7378   1.0000
   4.750   0.9509   0.01808   0.01093  -0.1028   0.7186   1.0000
   5.000   0.9804   0.01763   0.01051  -0.1020   0.6961   1.0000
   5.250   1.0097   0.01728   0.01017  -0.1012   0.6707   1.0000
   5.500   1.0369   0.01709   0.00997  -0.1001   0.6411   1.0000
   5.750   1.0613   0.01707   0.00989  -0.0986   0.6065   1.0000
   6.000   1.0839   0.01723   0.00991  -0.0969   0.5669   1.0000
   6.250   1.1028   0.01759   0.01010  -0.0947   0.5229   1.0000
   6.500   1.1184   0.01816   0.01044  -0.0921   0.4755   1.0000
   6.750   1.1317   0.01890   0.01092  -0.0893   0.4271   1.0000
   7.000   1.1437   0.01980   0.01153  -0.0864   0.3811   1.0000
   7.250   1.1550   0.02082   0.01227  -0.0836   0.3395   1.0000
   7.500   1.1668   0.02190   0.01312  -0.0810   0.3023   1.0000
   7.750   1.1795   0.02303   0.01404  -0.0786   0.2710   1.0000
   8.000   1.1934   0.02419   0.01502  -0.0765   0.2445   1.0000
   8.250   1.2087   0.02538   0.01604  -0.0746   0.2226   1.0000
   8.500   1.2253   0.02661   0.01718  -0.0730   0.2032   1.0000
   8.750   1.2430   0.02784   0.01838  -0.0717   0.1867   1.0000
   9.000   1.2622   0.02915   0.01965  -0.0705   0.1722   1.0000
   9.250   1.2825   0.03053   0.02099  -0.0697   0.1594   1.0000
   9.500   1.3067   0.03209   0.02245  -0.0695   0.1477   1.0000
   9.750   1.3226   0.03331   0.02386  -0.0678   0.1379   1.0000
  10.000   1.3432   0.03495   0.02560  -0.0671   0.1288   1.0000
  10.250   1.3693   0.03679   0.02731  -0.0674   0.1200   1.0000
  10.500   1.3800   0.03817   0.02905  -0.0649   0.1132   1.0000
  10.750   1.4046   0.04027   0.03109  -0.0651   0.1060   1.0000
  11.000   1.4130   0.04188   0.03306  -0.0624   0.1005   1.0000
  11.250   1.4416   0.04454   0.03557  -0.0634   0.0940   1.0000
  11.500   1.4403   0.04628   0.03781  -0.0594   0.0907   1.0000
  11.750   1.4457   0.04818   0.03999  -0.0566   0.0866   1.0000
  12.000   1.4688   0.05094   0.04270  -0.0570   0.0821   1.0000
  12.250   1.4628   0.05374   0.04591  -0.0531   0.0803   1.0000
  12.500   1.4508   0.05631   0.04889  -0.0487   0.0787   1.0000
  12.750   1.4388   0.05913   0.05207  -0.0449   0.0770   1.0000
  13.000   1.4282   0.06208   0.05531  -0.0418   0.0753   1.0000
  13.250   1.4213   0.06505   0.05849  -0.0395   0.0737   1.0000
  13.500   1.4160   0.06824   0.06186  -0.0377   0.0723   1.0000
  13.750   1.4062   0.07196   0.06577  -0.0361   0.0714   1.0000
  14.000   1.3910   0.07631   0.07034  -0.0348   0.0708   1.0000
  14.250   1.3673   0.08133   0.07563  -0.0340   0.0707   1.0000
  14.500   1.2720   0.09377   0.08875  -0.0371   0.0744   1.0000
  14.750   1.2071   0.10735   0.10259  -0.0441   0.0778   1.0000
  15.000   1.1624   0.12035   0.11571  -0.0519   0.0799   1.0000
  15.250   1.1297   0.13299   0.12838  -0.0592   0.0811   1.0000
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