Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 8K AIRFOIL (goe08k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.98 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe08k-il-1000000-n5.txt
Download as CSV file: xf-goe08k-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 8K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.3485   0.02991   0.02679  -0.2352   0.9101   0.0062
 -13.750  -0.3673   0.02711   0.02375  -0.2327   0.9033   0.0063
 -13.500  -0.3709   0.02535   0.02181  -0.2304   0.8985   0.0064
 -13.250  -0.3750   0.02346   0.01969  -0.2278   0.8942   0.0064
 -13.000  -0.3867   0.02277   0.01893  -0.2213   0.8899   0.0064
 -12.750  -0.4011   0.02172   0.01775  -0.2145   0.8853   0.0067
 -12.500  -0.3981   0.02072   0.01660  -0.2110   0.8821   0.0068
 -12.250  -0.3840   0.01976   0.01551  -0.2097   0.8796   0.0069
 -12.000  -0.3891   0.01913   0.01480  -0.2038   0.8762   0.0070
 -11.750  -0.3896   0.01849   0.01407  -0.1987   0.8726   0.0071
 -11.500  -0.3792   0.01787   0.01335  -0.1960   0.8698   0.0074
 -11.250  -0.3659   0.01718   0.01254  -0.1938   0.8674   0.0074
 -11.000  -0.3476   0.01654   0.01177  -0.1927   0.8653   0.0077
 -10.750  -0.3385   0.01603   0.01118  -0.1894   0.8629   0.0078
 -10.500  -0.3324   0.01560   0.01068  -0.1853   0.8600   0.0081
 -10.250  -0.3225   0.01514   0.01013  -0.1820   0.8570   0.0081
 -10.000  -0.3074   0.01469   0.00959  -0.1798   0.8543   0.0085
  -9.750  -0.2898   0.01417   0.00896  -0.1782   0.8520   0.0088
  -9.500  -0.2677   0.01367   0.00837  -0.1776   0.8498   0.0091
  -9.250  -0.2620   0.01340   0.00806  -0.1731   0.8470   0.0094
  -9.000  -0.2507   0.01310   0.00770  -0.1699   0.8441   0.0097
  -8.750  -0.2345   0.01282   0.00736  -0.1678   0.8414   0.0102
  -8.500  -0.2162   0.01249   0.00695  -0.1661   0.8389   0.0105
  -8.250  -0.1953   0.01215   0.00653  -0.1650   0.8367   0.0110
  -8.000  -0.1759   0.01185   0.00617  -0.1635   0.8344   0.0115
  -7.750  -0.1640   0.01163   0.00594  -0.1603   0.8315   0.0122
  -7.500  -0.1501   0.01143   0.00569  -0.1576   0.8281   0.0129
  -7.250  -0.1325   0.01123   0.00543  -0.1556   0.8251   0.0135
  -7.000  -0.1129   0.01093   0.00509  -0.1541   0.8224   0.0151
  -6.750  -0.0931   0.01073   0.00484  -0.1527   0.8198   0.0162
  -6.500  -0.0789   0.01058   0.00466  -0.1499   0.8167   0.0172
  -6.250  -0.0625   0.01038   0.00445  -0.1476   0.8135   0.0192
  -6.000  -0.0436   0.01022   0.00426  -0.1459   0.8105   0.0212
  -5.750  -0.0224   0.01006   0.00407  -0.1447   0.8078   0.0237
  -5.500  -0.0017   0.00994   0.00394  -0.1434   0.8052   0.0275
  -5.250   0.0150   0.00991   0.00394  -0.1412   0.8020   0.0303
  -5.000   0.0335   0.00988   0.00391  -0.1393   0.7987   0.0332
  -4.750   0.0537   0.00982   0.00381  -0.1379   0.7957   0.0345
  -4.500   0.0765   0.00978   0.00375  -0.1370   0.7930   0.0366
  -4.250   0.0984   0.00980   0.00378  -0.1359   0.7902   0.0388
  -4.000   0.1164   0.00974   0.00370  -0.1339   0.7869   0.0397
  -3.750   0.1377   0.00979   0.00375  -0.1327   0.7837   0.0420
  -3.500   0.1587   0.00974   0.00365  -0.1314   0.7806   0.0428
  -3.250   0.1820   0.00973   0.00360  -0.1307   0.7780   0.0438
  -3.000   0.2040   0.00978   0.00365  -0.1296   0.7755   0.0445
  -2.750   0.2217   0.00971   0.00355  -0.1276   0.7726   0.0447
  -2.500   0.2393   0.00958   0.00339  -0.1256   0.7696   0.0464
  -2.250   0.2593   0.00948   0.00328  -0.1241   0.7669   0.0478
  -2.000   0.2811   0.00941   0.00318  -0.1230   0.7644   0.0486
  -1.750   0.3038   0.00935   0.00309  -0.1221   0.7621   0.0492
  -1.500   0.3239   0.00932   0.00306  -0.1207   0.7599   0.0499
  -1.250   0.3446   0.00930   0.00303  -0.1194   0.7574   0.0507
  -1.000   0.3655   0.00926   0.00298  -0.1181   0.7549   0.0512
  -0.750   0.3871   0.00922   0.00292  -0.1170   0.7523   0.0514
  -0.500   0.4101   0.00921   0.00289  -0.1162   0.7500   0.0521
  -0.250   0.4344   0.00917   0.00283  -0.1157   0.7480   0.0527
   0.000   0.4556   0.00918   0.00283  -0.1145   0.7461   0.0530
   0.250   0.4757   0.00918   0.00285  -0.1131   0.7440   0.0535
   0.500   0.4971   0.00919   0.00286  -0.1119   0.7418   0.0541
   0.750   0.5186   0.00921   0.00288  -0.1109   0.7392   0.0546
   1.000   0.5403   0.00924   0.00289  -0.1098   0.7356   0.0549
   1.250   0.5651   0.00925   0.00288  -0.1095   0.7332   0.0559
   1.500   0.5861   0.00929   0.00294  -0.1083   0.7307   0.0561
   1.750   0.6052   0.00935   0.00301  -0.1067   0.7273   0.0564
   2.000   0.6265   0.00939   0.00306  -0.1056   0.7243   0.0595
   2.250   0.6490   0.00942   0.00312  -0.1048   0.7218   0.0659
   2.500   0.6728   0.00946   0.00317  -0.1042   0.7194   0.0678
   2.750   0.6997   0.00929   0.00330  -0.1047   0.7166   0.2070
   3.250   1.0466   0.00858   0.00474  -0.1750   0.7186   1.0000
   3.500   1.0620   0.00872   0.00489  -0.1726   0.7136   1.0000
   3.750   1.0771   0.00888   0.00505  -0.1702   0.7078   1.0000
   4.000   1.0866   0.00914   0.00529  -0.1665   0.6987   1.0000
   4.250   1.0964   0.00942   0.00553  -0.1629   0.6885   1.0000
   4.500   1.1164   0.00955   0.00568  -0.1616   0.6859   1.0000
   4.750   1.1302   0.00978   0.00593  -0.1590   0.6775   1.0000
   5.000   1.1414   0.01009   0.00623  -0.1558   0.6682   1.0000
   5.250   1.1513   0.01045   0.00656  -0.1524   0.6562   1.0000
   5.500   1.1650   0.01076   0.00688  -0.1498   0.6454   1.0000
   5.750   1.1525   0.01177   0.00772  -0.1418   0.6054   1.0000
   6.000   1.1227   0.01350   0.00915  -0.1306   0.5466   1.0000
   6.250   1.1188   0.01457   0.01007  -0.1249   0.5152   1.0000
   6.500   1.1141   0.01575   0.01109  -0.1192   0.4816   1.0000
   6.750   1.0970   0.01752   0.01256  -0.1114   0.4231   1.0000
   7.000   1.1080   0.01819   0.01317  -0.1088   0.4059   1.0000
   7.250   1.1072   0.01941   0.01422  -0.1043   0.3673   1.0000
   7.500   1.1025   0.02085   0.01542  -0.0992   0.3171   1.0000
   7.750   1.0978   0.02237   0.01668  -0.0942   0.2649   1.0000
   8.000   1.0971   0.02375   0.01782  -0.0901   0.2208   1.0000
   8.250   1.1016   0.02491   0.01882  -0.0869   0.1867   1.0000
   8.500   1.1052   0.02613   0.01985  -0.0836   0.1493   1.0000
   8.750   1.1043   0.02765   0.02112  -0.0797   0.0991   1.0000
   9.000   1.1133   0.02866   0.02203  -0.0774   0.0784   1.0000
   9.250   1.1249   0.02953   0.02286  -0.0755   0.0673   1.0000
   9.500   1.1368   0.03039   0.02370  -0.0737   0.0572   1.0000
   9.750   1.1466   0.03140   0.02462  -0.0716   0.0400   1.0000
  10.000   1.1570   0.03237   0.02554  -0.0696   0.0284   1.0000
  10.250   1.1683   0.03332   0.02647  -0.0678   0.0220   1.0000
  10.500   1.1808   0.03419   0.02735  -0.0663   0.0192   1.0000
  10.750   1.1941   0.03503   0.02820  -0.0648   0.0169   1.0000
  11.000   1.2055   0.03601   0.02919  -0.0632   0.0149   1.0000
  11.250   1.2183   0.03690   0.03011  -0.0617   0.0131   1.0000
  11.500   1.2311   0.03780   0.03102  -0.0603   0.0121   1.0000
  11.750   1.2433   0.03874   0.03199  -0.0589   0.0114   1.0000
  12.000   1.2550   0.03973   0.03301  -0.0574   0.0105   1.0000
  12.250   1.2669   0.04071   0.03402  -0.0560   0.0098   1.0000
  12.500   1.2774   0.04180   0.03515  -0.0545   0.0091   1.0000
  12.750   1.2885   0.04289   0.03627  -0.0530   0.0089   1.0000
  13.000   1.3002   0.04393   0.03736  -0.0517   0.0083   1.0000
  13.250   1.3113   0.04501   0.03847  -0.0504   0.0078   1.0000
  13.500   1.3207   0.04625   0.03976  -0.0489   0.0078   1.0000
  13.750   1.3298   0.04750   0.04104  -0.0474   0.0071   1.0000
  14.000   1.3397   0.04871   0.04230  -0.0461   0.0068   1.0000
  14.250   1.3490   0.04999   0.04365  -0.0447   0.0064   1.0000
  14.500   1.3578   0.05132   0.04502  -0.0434   0.0060   1.0000
  14.750   1.3659   0.05272   0.04645  -0.0420   0.0055   1.0000
  15.000   1.3730   0.05423   0.04802  -0.0406   0.0054   1.0000
  15.250   1.3799   0.05577   0.04961  -0.0392   0.0053   1.0000
  15.500   1.3867   0.05736   0.05126  -0.0379   0.0052   1.0000
  15.750   1.3950   0.05879   0.05276  -0.0368   0.0050   1.0000
  16.000   1.3999   0.06056   0.05459  -0.0354   0.0049   1.0000
  16.250   1.4046   0.06238   0.05648  -0.0341   0.0045   1.0000
  16.500   1.4122   0.06394   0.05811  -0.0331   0.0046   1.0000
  16.750   1.4166   0.06584   0.06007  -0.0320   0.0044   1.0000
  17.000   1.4193   0.06795   0.06226  -0.0307   0.0043   1.0000
  17.250   1.4228   0.06998   0.06434  -0.0297   0.0041   1.0000
  17.500   1.4239   0.07229   0.06672  -0.0285   0.0040   1.0000
  17.750   1.4252   0.07462   0.06913  -0.0275   0.0040   1.0000
  18.000   1.4257   0.07705   0.07164  -0.0265   0.0039   1.0000
  18.250   1.4296   0.07916   0.07384  -0.0259   0.0038   1.0000
  18.500   1.4283   0.08189   0.07666  -0.0251   0.0038   1.0000
  18.750   1.4300   0.08431   0.07917  -0.0244   0.0036   1.0000
  19.000   1.4290   0.08710   0.08205  -0.0239   0.0036   1.0000
<< Back to GOE 8K AIRFOIL (goe08k-il)

Polar data table (+)

Polar graphs


<< Back to GOE 8K AIRFOIL (goe08k-il)