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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 100,000
Max Cl/Cd: 60.29 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe379-il-100000-n5.txt
Download as CSV file: xf-goe379-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2928   0.10363   0.09919  -0.0296   1.0000   0.0290
  -7.500  -0.2955   0.10175   0.09740  -0.0291   1.0000   0.0290
  -7.250  -0.2990   0.10042   0.09617  -0.0297   1.0000   0.0291
  -7.000  -0.3013   0.09861   0.09445  -0.0293   1.0000   0.0291
  -6.750  -0.2966   0.09230   0.08819  -0.0237   1.0000   0.0302
  -6.500  -0.3026   0.09071   0.08668  -0.0221   1.0000   0.0303
  -6.250  -0.2858   0.08682   0.08280  -0.0252   0.9946   0.0316
  -6.000  -0.2593   0.08258   0.07854  -0.0315   0.9864   0.0327
  -5.750  -0.2313   0.07841   0.07433  -0.0381   0.9780   0.0341
  -5.500  -0.2014   0.07440   0.07027  -0.0452   0.9686   0.0359
  -5.250  -0.1580   0.07102   0.06675  -0.0568   0.9581   0.0377
  -5.000  -0.1179   0.06730   0.06283  -0.0651   0.9496   0.0380
  -4.750  -0.0820   0.06319   0.05858  -0.0710   0.9425   0.0381
  -4.500  -0.0545   0.05873   0.05405  -0.0744   0.9342   0.0383
  -4.250  -0.0191   0.05486   0.04997  -0.0788   0.9275   0.0381
  -4.000  -0.0069   0.04948   0.04465  -0.0783   0.9183   0.0280
  -3.750   0.0248   0.04577   0.04078  -0.0816   0.9106   0.0271
  -3.500   0.0580   0.04228   0.03708  -0.0846   0.9015   0.0274
  -3.250   0.0882   0.03901   0.03357  -0.0866   0.8920   0.0268
  -3.000   0.1225   0.03555   0.02982  -0.0888   0.8848   0.0259
  -2.750   0.1511   0.03255   0.02652  -0.0894   0.8741   0.0253
  -2.500   0.1810   0.02947   0.02306  -0.0897   0.8644   0.0253
  -2.250   0.2126   0.02638   0.01949  -0.0900   0.8558   0.0259
  -2.000   0.2423   0.02327   0.01572  -0.0894   0.8456   0.0287
  -1.750   0.2700   0.02131   0.01334  -0.0888   0.8341   0.0308
  -1.500   0.2986   0.01971   0.01129  -0.0883   0.8219   0.0347
  -1.250   0.3270   0.01867   0.00993  -0.0878   0.8090   0.0435
  -1.000   0.3552   0.01766   0.00863  -0.0872   0.7961   0.0563
  -0.750   0.3828   0.01710   0.00780  -0.0867   0.7833   0.0740
  -0.500   0.4102   0.01654   0.00707  -0.0863   0.7708   0.0864
  -0.250   0.4375   0.01597   0.00637  -0.0858   0.7584   0.0937
   0.000   0.4639   0.01564   0.00592  -0.0853   0.7451   0.1057
   0.250   0.4921   0.01532   0.00546  -0.0851   0.7315   0.1147
   0.500   0.5194   0.01508   0.00511  -0.0848   0.7178   0.1262
   0.750   0.5462   0.01489   0.00489  -0.0844   0.7040   0.1498
   1.000   0.5728   0.01463   0.00470  -0.0841   0.6901   0.2084
   1.500   0.6623   0.01319   0.00440  -0.0913   0.6598   1.0000
   1.750   0.6869   0.01334   0.00438  -0.0905   0.6452   1.0000
   2.000   0.7115   0.01351   0.00440  -0.0898   0.6308   1.0000
   2.250   0.7360   0.01369   0.00445  -0.0890   0.6164   1.0000
   2.500   0.7603   0.01388   0.00455  -0.0882   0.6020   1.0000
   2.750   0.7846   0.01409   0.00466  -0.0874   0.5878   1.0000
   3.000   0.8087   0.01431   0.00480  -0.0866   0.5739   1.0000
   3.250   0.8328   0.01455   0.00498  -0.0858   0.5604   1.0000
   3.500   0.8568   0.01481   0.00522  -0.0851   0.5470   1.0000
   3.750   0.8806   0.01508   0.00546  -0.0843   0.5337   1.0000
   4.000   0.9043   0.01537   0.00572  -0.0835   0.5205   1.0000
   4.250   0.9278   0.01566   0.00601  -0.0827   0.5069   1.0000
   4.500   0.9510   0.01597   0.00636  -0.0818   0.4927   1.0000
   4.750   0.9738   0.01629   0.00669  -0.0808   0.4778   1.0000
   5.000   0.9965   0.01661   0.00704  -0.0799   0.4632   1.0000
   5.250   1.0193   0.01695   0.00747  -0.0790   0.4499   1.0000
   5.500   1.0423   0.01730   0.00791  -0.0781   0.4387   1.0000
   5.750   1.0653   0.01768   0.00838  -0.0773   0.4284   1.0000
   6.000   1.0882   0.01805   0.00893  -0.0764   0.4175   1.0000
   6.250   1.1066   0.01839   0.00928  -0.0747   0.3906   1.0000
   6.500   1.1225   0.01885   0.00970  -0.0726   0.3557   1.0000
   6.750   1.1358   0.01952   0.01021  -0.0703   0.3036   1.0000
   7.000   1.1449   0.02072   0.01094  -0.0674   0.2109   1.0000
   7.250   1.1361   0.02396   0.01288  -0.0629   0.0429   1.0000
   7.500   1.1429   0.02576   0.01456  -0.0599   0.0240   1.0000
   7.750   1.1545   0.02704   0.01606  -0.0574   0.0207   1.0000
   8.000   1.1630   0.02848   0.01774  -0.0547   0.0190   1.0000
   8.250   1.1676   0.03008   0.01958  -0.0515   0.0175   1.0000
   8.500   1.1719   0.03143   0.02115  -0.0484   0.0164   1.0000
   8.750   1.1734   0.03296   0.02290  -0.0451   0.0155   1.0000
   9.000   1.1716   0.03480   0.02502  -0.0418   0.0150   1.0000
   9.250   1.1694   0.03679   0.02720  -0.0389   0.0146   1.0000
   9.500   1.1678   0.03892   0.02948  -0.0365   0.0143   1.0000
   9.750   1.1664   0.04121   0.03190  -0.0343   0.0140   1.0000
  10.000   1.1679   0.04350   0.03430  -0.0324   0.0138   1.0000
  10.250   1.1728   0.04572   0.03661  -0.0306   0.0131   1.0000
  10.500   1.1820   0.04782   0.03879  -0.0290   0.0126   1.0000
  10.750   1.1925   0.05024   0.04127  -0.0274   0.0115   1.0000
  11.000   1.2108   0.05301   0.04413  -0.0260   0.0108   1.0000
  11.250   1.2277   0.05601   0.04734  -0.0248   0.0107   1.0000
  11.500   1.2376   0.05932   0.05091  -0.0235   0.0106   1.0000
  11.750   1.2404   0.06270   0.05456  -0.0223   0.0106   1.0000
  12.000   1.2383   0.06625   0.05839  -0.0212   0.0107   1.0000
  12.250   1.2336   0.06947   0.06187  -0.0205   0.0108   1.0000
  12.500   1.2260   0.07326   0.06593  -0.0200   0.0108   1.0000
  12.750   1.2165   0.07730   0.07024  -0.0201   0.0109   1.0000
  13.000   1.2051   0.08174   0.07494  -0.0206   0.0109   1.0000
  13.250   1.1932   0.08632   0.07975  -0.0216   0.0110   1.0000
  13.500   1.1804   0.09122   0.08489  -0.0231   0.0111   1.0000
  13.750   1.1655   0.09679   0.09070  -0.0253   0.0112   1.0000
  14.000   1.1511   0.10248   0.09660  -0.0280   0.0113   1.0000
  14.250   1.1360   0.10874   0.10307  -0.0312   0.0114   1.0000
  14.500   1.1215   0.11530   0.10982  -0.0350   0.0116   1.0000
  14.750   1.1055   0.12267   0.11738  -0.0394   0.0117   1.0000
  15.000   1.0902   0.13043   0.12532  -0.0444   0.0118   1.0000
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