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GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 12K AIRFOIL (goe12k-il)
Reynolds number: 100,000
Max Cl/Cd: 42.28 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe12k-il-100000.txt
Download as CSV file: xf-goe12k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 12K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5418   0.11265   0.10804  -0.0205   1.0000   0.1138
  -7.750  -0.5768   0.11114   0.10661  -0.0198   1.0000   0.1143
  -7.500  -0.6110   0.10839   0.10383  -0.0232   1.0000   0.1149
  -7.250  -0.5878   0.10345   0.09898  -0.0172   1.0000   0.1170
  -7.000  -0.5732   0.10121   0.09674  -0.0130   1.0000   0.1211
  -6.750  -0.5825   0.09848   0.09402  -0.0123   1.0000   0.1247
  -6.500  -0.6062   0.09485   0.09034  -0.0167   1.0000   0.1293
  -6.250  -0.6155   0.08984   0.08526  -0.0178   1.0000   0.1319
  -6.000  -0.6066   0.08730   0.08279  -0.0136   1.0000   0.1343
  -5.750  -0.6031   0.08466   0.08013  -0.0119   1.0000   0.1381
  -5.500  -0.6110   0.07969   0.07480  -0.0174   1.0000   0.1475
  -5.250  -0.6027   0.07660   0.07185  -0.0140   1.0000   0.1496
  -5.000  -0.5951   0.07439   0.06965  -0.0116   1.0000   0.1551
  -4.750  -0.5908   0.07027   0.06529  -0.0132   1.0000   0.1654
  -4.500  -0.5817   0.06791   0.06296  -0.0109   1.0000   0.1702
  -4.250  -0.5734   0.06447   0.05925  -0.0116   1.0000   0.1819
  -4.000  -0.5629   0.06219   0.05700  -0.0094   1.0000   0.1874
  -3.750  -0.5532   0.05950   0.05418  -0.0085   1.0000   0.2011
  -3.500  -0.5423   0.05713   0.05164  -0.0075   1.0000   0.2159
  -3.250  -0.5309   0.05511   0.04948  -0.0061   1.0000   0.2317
  -3.000  -0.5194   0.05318   0.04746  -0.0044   1.0000   0.2481
  -2.750  -0.5082   0.05127   0.04551  -0.0023   1.0000   0.2654
  -2.500  -0.4975   0.04944   0.04371   0.0002   1.0000   0.2842
  -2.250  -0.4499   0.03944   0.03080  -0.0011   1.0000   0.1305
  -2.000  -0.4333   0.03755   0.02868   0.0007   1.0000   0.1302
  -1.750  -0.4162   0.03574   0.02671   0.0024   1.0000   0.1288
  -1.500  -0.3981   0.03442   0.02514   0.0041   1.0000   0.1280
  -1.250  -0.3793   0.03350   0.02393   0.0058   1.0000   0.1286
  -1.000  -0.3601   0.03292   0.02307   0.0074   1.0000   0.1299
  -0.750  -0.3405   0.03226   0.02219   0.0089   1.0000   0.1307
  -0.500  -0.3202   0.03138   0.02117   0.0101   1.0000   0.1315
  -0.250  -0.2995   0.03077   0.02048   0.0111   1.0000   0.1328
   0.000  -0.2790   0.03042   0.02012   0.0121   1.0000   0.1357
   0.250  -0.2582   0.03021   0.01988   0.0130   1.0000   0.1394
   0.500  -0.2369   0.03007   0.01966   0.0140   1.0000   0.1426
   0.750  -0.2155   0.03001   0.01951   0.0148   1.0000   0.1454
   1.000  -0.1937   0.02987   0.01943   0.0155   1.0000   0.1488
   1.250  -0.1664   0.03020   0.01988   0.0151   0.9983   0.1554
   1.500  -0.1355   0.03094   0.02065   0.0140   0.9957   0.1651
   1.750  -0.1082   0.03150   0.02132   0.0135   0.9937   0.1804
   2.000   0.0603   0.03332   0.02557  -0.0174   0.9999   1.0000
   2.250   0.0933   0.03450   0.02662  -0.0196   0.9956   1.0000
   2.500   0.1251   0.03548   0.02751  -0.0215   0.9892   1.0000
   2.750   0.1612   0.03662   0.02859  -0.0243   0.9798   1.0000
   3.000   0.2467   0.03757   0.02946  -0.0356   0.9346   1.0000
   3.250   0.3032   0.03830   0.03015  -0.0411   0.9153   1.0000
   3.500   0.3443   0.03867   0.03052  -0.0437   0.9004   1.0000
   3.750   0.3807   0.03886   0.03071  -0.0454   0.8856   1.0000
   4.000   0.4141   0.03899   0.03088  -0.0466   0.8713   1.0000
   4.250   0.4472   0.03911   0.03104  -0.0476   0.8575   1.0000
   4.500   0.4828   0.03915   0.03114  -0.0489   0.8437   1.0000
   4.750   0.5201   0.03907   0.03114  -0.0504   0.8303   1.0000
   5.000   0.5594   0.03880   0.03096  -0.0520   0.8170   1.0000
   5.250   0.6028   0.03802   0.03029  -0.0538   0.8022   1.0000
   5.500   0.6622   0.03570   0.02809  -0.0566   0.7835   1.0000
   5.750   0.7289   0.03237   0.02491  -0.0597   0.7655   1.0000
   6.750   0.8486   0.02669   0.01981  -0.0538   0.6839   1.0000
   7.000   0.8640   0.02602   0.01923  -0.0502   0.6385   1.0000
   7.250   0.9462   0.02238   0.01415  -0.0539   0.4208   1.0000
   7.500   0.9366   0.02423   0.01515  -0.0475   0.2870   1.0000
   7.750   0.9369   0.02609   0.01617  -0.0433   0.2130   1.0000
   8.000   0.9497   0.02740   0.01721  -0.0410   0.1851   1.0000
   8.250   0.9675   0.02862   0.01818  -0.0395   0.1676   1.0000
   8.500   0.9894   0.02961   0.01910  -0.0386   0.1544   1.0000
   8.750   1.0154   0.03064   0.02011  -0.0383   0.1430   1.0000
   9.000   1.0476   0.03186   0.02128  -0.0391   0.1326   1.0000
   9.250   1.0874   0.03337   0.02263  -0.0413   0.1219   1.0000
   9.500   1.1111   0.03451   0.02396  -0.0407   0.1139   1.0000
   9.750   1.1534   0.03653   0.02601  -0.0435   0.1052   1.0000
  10.000   1.1811   0.03813   0.02773  -0.0437   0.0984   1.0000
  10.250   1.2171   0.04080   0.03060  -0.0455   0.0918   1.0000
  10.500   1.2343   0.04247   0.03251  -0.0439   0.0870   1.0000
  10.750   1.2797   0.04666   0.03677  -0.0483   0.0815   1.0000
  11.000   1.2751   0.04810   0.03863  -0.0426   0.0799   1.0000
  11.250   1.2731   0.05018   0.04112  -0.0378   0.0779   1.0000
  11.500   1.2717   0.05229   0.04355  -0.0334   0.0757   1.0000
  11.750   1.2723   0.05462   0.04613  -0.0297   0.0740   1.0000
  12.000   1.2726   0.05727   0.04902  -0.0262   0.0728   1.0000
  12.250   1.2903   0.06067   0.05243  -0.0260   0.0704   1.0000
  12.500   1.2854   0.06542   0.05744  -0.0228   0.0696   1.0000
  12.750   1.2640   0.06787   0.06017  -0.0168   0.0693   1.0000
  13.000   1.2396   0.07031   0.06291  -0.0109   0.0690   1.0000
  13.250   1.2179   0.07355   0.06642  -0.0063   0.0689   1.0000
  13.500   1.1935   0.07692   0.07005  -0.0021   0.0689   1.0000
  13.750   1.1728   0.08106   0.07439   0.0010   0.0691   1.0000
  14.000   1.1468   0.08534   0.07889   0.0037   0.0691   1.0000
  14.250   1.1308   0.09080   0.08448   0.0051   0.0695   1.0000
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