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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 100,000
Max Cl/Cd: 55.74 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe431-il-100000-n5.txt
Download as CSV file: xf-goe431-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 431 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1046   0.09928   0.09414  -0.0958   0.9374   0.0302
  -9.500  -0.1005   0.09541   0.09028  -0.0979   0.9331   0.0302
  -9.250  -0.1038   0.09073   0.08563  -0.1001   0.9271   0.0311
  -9.000  -0.1024   0.08499   0.07990  -0.1041   0.9234   0.0315
  -8.750  -0.1126   0.07804   0.07297  -0.1083   0.9184   0.0318
  -8.500  -0.1251   0.07456   0.06953  -0.1081   0.9109   0.0316
  -8.250  -0.1445   0.06673   0.06168  -0.1138   0.9055   0.0316
  -8.000  -0.1700   0.06372   0.05870  -0.1121   0.8953   0.0314
  -7.750  -0.1746   0.05260   0.04730  -0.1273   0.8902   0.0313
  -7.500  -0.1868   0.04837   0.04293  -0.1302   0.8811   0.0313
  -7.250  -0.1567   0.04172   0.03589  -0.1425   0.8784   0.0323
  -7.000  -0.1241   0.03891   0.03294  -0.1483   0.8768   0.0340
  -6.750  -0.0830   0.03526   0.02895  -0.1569   0.8758   0.0374
  -6.500  -0.0584   0.03317   0.02658  -0.1602   0.8725   0.0406
  -6.250  -0.0353   0.03173   0.02500  -0.1622   0.8687   0.0443
  -6.000  -0.0011   0.02993   0.02290  -0.1660   0.8667   0.0506
  -5.750   0.0360   0.02797   0.02066  -0.1706   0.8653   0.0619
  -5.500   0.0721   0.02643   0.01918  -0.1744   0.8642   0.0825
  -5.250   0.0995   0.02733   0.02033  -0.1741   0.8626   0.1152
  -5.000   0.1308   0.02781   0.02044  -0.1749   0.8613   0.1429
  -4.750   0.1610   0.02833   0.02080  -0.1752   0.8602   0.1563
  -4.500   0.1695   0.02865   0.02076  -0.1727   0.8547   0.1652
  -4.250   0.1919   0.02909   0.02131  -0.1715   0.8510   0.1711
  -4.000   0.2298   0.02866   0.02046  -0.1735   0.8483   0.1813
  -3.750   0.2690   0.02859   0.02052  -0.1748   0.8458   0.1893
  -3.500   0.2856   0.02863   0.02030  -0.1733   0.8390   0.1963
  -3.250   0.3205   0.02807   0.01965  -0.1743   0.8343   0.2009
  -3.000   0.3650   0.02715   0.01854  -0.1770   0.8316   0.2042
  -2.750   0.4125   0.02611   0.01726  -0.1803   0.8297   0.2065
  -2.500   0.4182   0.02634   0.01740  -0.1767   0.8212   0.2073
  -2.250   0.4556   0.02566   0.01651  -0.1783   0.8180   0.2089
  -2.000   0.4970   0.02492   0.01558  -0.1806   0.8157   0.2105
  -1.750   0.5247   0.02463   0.01515  -0.1805   0.8112   0.2120
  -1.500   0.5442   0.02457   0.01497  -0.1790   0.8045   0.2133
  -1.250   0.5818   0.02399   0.01438  -0.1804   0.8013   0.2154
  -1.000   0.6228   0.02334   0.01370  -0.1824   0.7988   0.2181
  -0.750   0.6318   0.02366   0.01403  -0.1791   0.7900   0.2199
  -0.500   0.6674   0.02316   0.01348  -0.1801   0.7859   0.2225
  -0.250   0.7083   0.02250   0.01275  -0.1820   0.7829   0.2254
   0.000   0.7190   0.02270   0.01295  -0.1788   0.7728   0.2274
   0.250   0.7581   0.02206   0.01231  -0.1803   0.7682   0.2306
   0.500   0.7722   0.02215   0.01246  -0.1777   0.7586   0.2331
   1.000   0.8207   0.02172   0.01208  -0.1757   0.7418   0.2415
   1.250   0.8546   0.02121   0.01161  -0.1762   0.7341   0.2477
   1.750   0.8831   0.02140   0.01191  -0.1709   0.7072   0.2612
   2.250   0.9077   0.02194   0.01260  -0.1654   0.6666   0.2793
   2.500   0.9268   0.02194   0.01263  -0.1636   0.6346   0.2938
   2.750   0.9769   0.02049   0.01106  -0.1660   0.5880   0.3255
   3.000   1.0241   0.01961   0.00980  -0.1681   0.5378   0.3724
   3.250   1.0475   0.01992   0.00993  -0.1671   0.5076   0.4195
   3.500   1.0690   0.02034   0.01028  -0.1659   0.4877   0.4724
   4.000   1.1155   0.02109   0.01099  -0.1642   0.4613   0.5668
   4.250   1.1404   0.02135   0.01130  -0.1637   0.4521   0.6121
   4.500   1.1631   0.02127   0.01157  -0.1626   0.4444   0.7431
   4.750   1.1867   0.02152   0.01181  -0.1619   0.4377   1.0000
   5.000   1.2132   0.02194   0.01218  -0.1617   0.4314   1.0000
   5.250   1.2417   0.02239   0.01252  -0.1619   0.4262   1.0000
   5.500   1.2683   0.02282   0.01296  -0.1618   0.4210   1.0000
   5.750   1.2945   0.02326   0.01341  -0.1616   0.4159   1.0000
   6.000   1.3224   0.02374   0.01385  -0.1618   0.4114   1.0000
   6.250   1.3506   0.02423   0.01436  -0.1620   0.4075   1.0000
   6.500   1.3756   0.02471   0.01492  -0.1616   0.4032   1.0000
   6.750   1.4005   0.02522   0.01547  -0.1613   0.3985   1.0000
   7.000   1.4276   0.02577   0.01599  -0.1613   0.3938   1.0000
   7.250   1.4482   0.02629   0.01665  -0.1602   0.3886   1.0000
   7.500   1.4699   0.02683   0.01728  -0.1593   0.3833   1.0000
   7.750   1.4947   0.02738   0.01786  -0.1590   0.3788   1.0000
   8.000   1.5164   0.02796   0.01855  -0.1581   0.3742   1.0000
   8.250   1.5355   0.02854   0.01930  -0.1568   0.3693   1.0000
   8.500   1.5574   0.02912   0.01999  -0.1560   0.3648   1.0000
   8.750   1.5819   0.02973   0.02063  -0.1556   0.3605   1.0000
   9.000   1.5946   0.03038   0.02152  -0.1533   0.3551   1.0000
   9.250   1.6109   0.03100   0.02229  -0.1516   0.3495   1.0000
   9.500   1.6262   0.03163   0.02301  -0.1497   0.3430   1.0000
   9.750   1.6306   0.03236   0.02395  -0.1463   0.3345   1.0000
  10.000   1.6358   0.03310   0.02476  -0.1430   0.3251   1.0000
  10.250   1.6362   0.03397   0.02574  -0.1393   0.3142   1.0000
  10.500   1.6359   0.03501   0.02695  -0.1356   0.3025   1.0000
  10.750   1.6362   0.03614   0.02822  -0.1323   0.2899   1.0000
  11.000   1.6364   0.03741   0.02964  -0.1292   0.2757   1.0000
  11.250   1.6370   0.03883   0.03122  -0.1264   0.2582   1.0000
  11.500   1.6369   0.04045   0.03297  -0.1237   0.2327   1.0000
  11.750   1.6282   0.04278   0.03511  -0.1205   0.1932   1.0000
  12.000   1.6129   0.04608   0.03812  -0.1172   0.1646   1.0000
  12.250   1.5997   0.04965   0.04156  -0.1145   0.1416   1.0000
  12.500   1.5875   0.05340   0.04527  -0.1123   0.1154   1.0000
  12.750   1.5708   0.05786   0.04964  -0.1103   0.0845   1.0000
  13.000   1.5489   0.06320   0.05486  -0.1087   0.0607   1.0000
  13.250   1.5292   0.06867   0.06033  -0.1078   0.0500   1.0000
  13.500   1.5109   0.07435   0.06609  -0.1075   0.0442   1.0000
  13.750   1.4946   0.08015   0.07203  -0.1077   0.0403   1.0000
  14.000   1.4781   0.08636   0.07840  -0.1086   0.0376   1.0000
  14.250   1.4616   0.09296   0.08514  -0.1100   0.0358   1.0000
  14.500   1.4472   0.09946   0.09180  -0.1117   0.0342   1.0000
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