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GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 574 AIRFOIL (goe574-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.85 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe574-il-1000000.txt
Download as CSV file: xf-goe574-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 574 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2097   0.10103   0.09955  -0.0431   0.9935   0.0105
  -9.750  -0.2038   0.09634   0.09486  -0.0465   0.9920   0.0114
  -9.500  -0.1977   0.09185   0.09037  -0.0495   0.9905   0.0114
  -9.250  -0.1888   0.08734   0.08586  -0.0528   0.9890   0.0115
  -9.000  -0.1797   0.08243   0.08095  -0.0563   0.9877   0.0115
  -8.750  -0.1691   0.07759   0.07611  -0.0601   0.9865   0.0115
  -8.500  -0.1597   0.07252   0.07104  -0.0639   0.9856   0.0116
  -8.250  -0.1567   0.06841   0.06694  -0.0656   0.9819   0.0116
  -8.000  -0.1621   0.06199   0.06054  -0.0685   0.9782   0.0119
  -7.750  -0.1489   0.05824   0.05679  -0.0718   0.9755   0.0121
  -7.500  -0.1476   0.05589   0.05445  -0.0717   0.9676   0.0125
  -6.750  -0.2065   0.05877   0.05719  -0.0792   0.9514   0.0122
  -6.500  -0.2004   0.05611   0.05449  -0.0788   0.9214   0.0124
  -6.250  -0.1536   0.05117   0.04942  -0.0886   0.9064   0.0137
  -5.750  -0.0767   0.01993   0.01645  -0.1103   0.8541   0.0127
  -5.500  -0.0426   0.01839   0.01451  -0.1125   0.8219   0.0137
  -5.250  -0.0322   0.01528   0.01077  -0.1090   0.8000   0.0149
  -5.000  -0.0103   0.01488   0.01011  -0.1076   0.7816   0.0158
  -4.750   0.0042   0.01324   0.00816  -0.1050   0.7654   0.0169
  -4.500   0.0267   0.01337   0.00823  -0.1040   0.7484   0.0176
  -4.250   0.0486   0.01337   0.00816  -0.1028   0.7309   0.0185
  -4.000   0.0693   0.01297   0.00759  -0.1013   0.7143   0.0197
  -3.750   0.0910   0.01273   0.00718  -0.0998   0.6978   0.0209
  -3.250   0.1319   0.01126   0.00535  -0.0967   0.6657   0.0234
  -3.000   0.1546   0.01116   0.00518  -0.0957   0.6490   0.0248
  -2.750   0.1775   0.01083   0.00473  -0.0946   0.6325   0.0259
  -2.500   0.2006   0.01053   0.00432  -0.0936   0.6160   0.0271
  -2.250   0.2240   0.01032   0.00399  -0.0926   0.5998   0.0282
  -2.000   0.2481   0.01028   0.00386  -0.0918   0.5834   0.0293
  -1.750   0.2718   0.01012   0.00358  -0.0909   0.5673   0.0297
  -1.500   0.2955   0.00996   0.00332  -0.0900   0.5513   0.0301
  -1.250   0.3174   0.00955   0.00282  -0.0887   0.5361   0.0304
  -1.000   0.3385   0.00920   0.00237  -0.0873   0.5220   0.0311
  -0.500   0.3834   0.00885   0.00185  -0.0849   0.4984   0.0335
  -0.250   0.4070   0.00878   0.00172  -0.0840   0.4890   0.0349
   0.000   0.4306   0.00876   0.00164  -0.0832   0.4806   0.0358
   0.250   0.4549   0.00872   0.00156  -0.0824   0.4739   0.0366
   0.500   0.4788   0.00872   0.00151  -0.0816   0.4676   0.0372
   0.750   0.5032   0.00871   0.00148  -0.0809   0.4626   0.0381
   1.000   0.5275   0.00871   0.00145  -0.0801   0.4578   0.0401
   1.250   0.5512   0.00873   0.00146  -0.0793   0.4531   0.0506
   1.500   0.5700   0.00835   0.00155  -0.0775   0.4497   0.2436
   1.750   0.5602   0.00703   0.00169  -0.0695   0.4471   0.7853
   2.000   0.8285   0.00780   0.00265  -0.1250   0.4358   1.0000
   2.250   0.8516   0.00785   0.00271  -0.1241   0.4319   1.0000
   2.500   0.8742   0.00793   0.00277  -0.1230   0.4283   1.0000
   2.750   0.8961   0.00804   0.00285  -0.1219   0.4245   1.0000
   3.000   0.9190   0.00809   0.00289  -0.1209   0.4180   1.0000
   3.250   0.9412   0.00817   0.00297  -0.1198   0.4131   1.0000
   3.500   0.9626   0.00829   0.00307  -0.1185   0.4083   1.0000
   3.750   0.9856   0.00833   0.00312  -0.1176   0.4023   1.0000
   4.000   1.0066   0.00846   0.00321  -0.1163   0.3949   1.0000
   4.250   1.0291   0.00851   0.00329  -0.1152   0.3868   1.0000
   4.500   1.0503   0.00862   0.00338  -0.1139   0.3777   1.0000
   4.750   1.0701   0.00880   0.00346  -0.1124   0.3532   1.0000
   5.000   1.0763   0.00977   0.00387  -0.1083   0.2495   1.0000
   5.250   1.0657   0.01160   0.00490  -0.1009   0.1005   1.0000
   5.500   1.0667   0.01266   0.00564  -0.0955   0.0192   1.0000
   5.750   1.0824   0.01296   0.00597  -0.0931   0.0168   1.0000
   6.000   1.0966   0.01331   0.00637  -0.0903   0.0145   1.0000
   6.250   1.1088   0.01367   0.00680  -0.0871   0.0132   1.0000
   6.500   1.1207   0.01393   0.00709  -0.0839   0.0125   1.0000
   6.750   1.1310   0.01426   0.00747  -0.0803   0.0119   1.0000
   7.000   1.1415   0.01461   0.00788  -0.0769   0.0113   1.0000
   7.250   1.1507   0.01503   0.00835  -0.0732   0.0108   1.0000
   7.500   1.1605   0.01547   0.00884  -0.0698   0.0103   1.0000
   7.750   1.1682   0.01603   0.00946  -0.0660   0.0099   1.0000
   8.000   1.1699   0.01684   0.01037  -0.0611   0.0094   1.0000
   8.250   1.1623   0.01808   0.01174  -0.0547   0.0090   1.0000
   8.500   1.1698   0.01876   0.01249  -0.0513   0.0087   1.0000
   8.750   1.1797   0.01936   0.01314  -0.0484   0.0085   1.0000
   9.000   1.1901   0.01998   0.01382  -0.0457   0.0081   1.0000
   9.250   1.1897   0.02116   0.01508  -0.0414   0.0079   1.0000
   9.500   1.1981   0.02197   0.01594  -0.0388   0.0077   1.0000
   9.750   1.1983   0.02330   0.01736  -0.0352   0.0076   1.0000
  10.000   1.2044   0.02440   0.01851  -0.0327   0.0072   1.0000
  10.250   1.2088   0.02569   0.01986  -0.0303   0.0069   1.0000
  10.500   1.2033   0.02787   0.02215  -0.0269   0.0071   1.0000
  10.750   1.2112   0.02913   0.02345  -0.0255   0.0068   1.0000
  11.000   1.2176   0.03059   0.02497  -0.0241   0.0065   1.0000
  11.250   1.2184   0.03261   0.02704  -0.0222   0.0063   1.0000
  11.500   1.2202   0.03464   0.02917  -0.0201   0.0065   1.0000
  11.750   1.2232   0.03658   0.03112  -0.0185   0.0061   1.0000
  12.000   1.2295   0.03868   0.03333  -0.0157   0.0057   1.0000
  12.250   1.2363   0.04029   0.03504  -0.0147   0.0055   1.0000
  12.500   1.2471   0.04200   0.03685  -0.0131   0.0055   1.0000
  12.750   1.2554   0.04374   0.03869  -0.0119   0.0054   1.0000
  13.000   1.2641   0.04573   0.04083  -0.0104   0.0051   1.0000
  13.250   1.2724   0.04808   0.04333  -0.0088   0.0052   1.0000
  13.500   1.2759   0.05058   0.04599  -0.0076   0.0052   1.0000
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