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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 100,000
Max Cl/Cd: 58.66 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe101-il-100000.txt
Download as CSV file: xf-goe101-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3914   0.10754   0.10259  -0.0150   1.0000   0.0509
  -8.500  -0.3927   0.10613   0.10126  -0.0179   1.0000   0.0514
  -8.250  -0.3962   0.10475   0.09998  -0.0209   1.0000   0.0517
  -8.000  -0.3947   0.10265   0.09794  -0.0251   1.0000   0.0519
  -7.750  -0.3822   0.09516   0.09047  -0.0202   1.0000   0.0534
  -7.500  -0.3712   0.09112   0.08644  -0.0187   1.0000   0.0555
  -7.250  -0.3675   0.08822   0.08360  -0.0190   1.0000   0.0575
  -7.000  -0.3627   0.08536   0.08079  -0.0205   1.0000   0.0593
  -6.750  -0.3571   0.08243   0.07791  -0.0231   1.0000   0.0617
  -6.500  -0.3473   0.08004   0.07553  -0.0305   1.0000   0.0645
  -6.250  -0.3303   0.07821   0.07352  -0.0403   1.0000   0.0654
  -6.000  -0.3310   0.07227   0.06783  -0.0338   1.0000   0.0672
  -5.750  -0.3249   0.06931   0.06491  -0.0310   1.0000   0.0711
  -5.500  -0.3115   0.06636   0.06193  -0.0341   1.0000   0.0764
  -5.250  -0.2938   0.06262   0.05805  -0.0399   1.0000   0.0805
  -5.000  -0.2890   0.05958   0.05513  -0.0367   1.0000   0.0836
  -4.750  -0.2592   0.05844   0.05347  -0.0440   1.0000   0.0933
  -4.500  -0.2585   0.05340   0.04875  -0.0405   1.0000   0.0954
  -4.250  -0.2502   0.05091   0.04633  -0.0387   1.0000   0.1008
  -4.000  -0.2328   0.04801   0.04324  -0.0406   1.0000   0.1100
  -3.750  -0.2154   0.04607   0.04106  -0.0417   1.0000   0.1226
  -3.500  -0.2104   0.04347   0.03865  -0.0392   1.0000   0.1293
  -3.250  -0.1981   0.04153   0.03662  -0.0390   1.0000   0.1450
  -3.000  -0.1572   0.03853   0.03338  -0.0445   0.9930   0.1807
  -2.750  -0.1148   0.03544   0.03028  -0.0490   0.9834   0.2249
  -2.500  -0.0786   0.03299   0.02792  -0.0516   0.9720   0.2960
  -2.250  -0.0508   0.03058   0.02577  -0.0510   0.9599   0.3836
  -2.000  -0.0185   0.02821   0.02352  -0.0508   0.9478   0.4669
  -1.750   0.1122   0.02294   0.01516  -0.0690   0.9428   0.1170
  -1.500   0.1620   0.02126   0.01291  -0.0718   0.9303   0.1055
  -1.250   0.2074   0.01951   0.01092  -0.0744   0.9165   0.1002
  -1.000   0.2504   0.01824   0.00943  -0.0762   0.9010   0.0979
  -0.750   0.2888   0.01723   0.00836  -0.0774   0.8834   0.1009
  -0.500   0.3205   0.01656   0.00762  -0.0773   0.8614   0.1058
  -0.250   0.3511   0.01587   0.00687  -0.0768   0.8418   0.1078
   0.000   0.3773   0.01534   0.00634  -0.0758   0.8192   0.1128
   0.250   0.4049   0.01505   0.00589  -0.0749   0.7997   0.1221
   0.500   0.4316   0.01469   0.00558  -0.0741   0.7796   0.1564
   0.750   0.4688   0.01266   0.00529  -0.0752   0.7622   1.0000
   1.000   0.4946   0.01292   0.00525  -0.0744   0.7455   1.0000
   1.250   0.5204   0.01319   0.00531  -0.0736   0.7301   1.0000
   1.500   0.5461   0.01349   0.00544  -0.0730   0.7159   1.0000
   1.750   0.5719   0.01382   0.00565  -0.0725   0.7027   1.0000
   2.000   0.5978   0.01415   0.00588  -0.0720   0.6904   1.0000
   2.250   0.6237   0.01450   0.00615  -0.0715   0.6793   1.0000
   2.500   0.6499   0.01484   0.00640  -0.0711   0.6695   1.0000
   2.750   0.6757   0.01520   0.00676  -0.0707   0.6587   1.0000
   3.000   0.7012   0.01556   0.00711  -0.0702   0.6476   1.0000
   3.250   0.7265   0.01586   0.00738  -0.0695   0.6356   1.0000
   3.500   0.7516   0.01612   0.00761  -0.0688   0.6225   1.0000
   3.750   0.7769   0.01638   0.00788  -0.0680   0.6100   1.0000
   4.000   0.8028   0.01667   0.00813  -0.0674   0.5995   1.0000
   4.250   0.8278   0.01698   0.00852  -0.0667   0.5874   1.0000
   4.500   0.8527   0.01730   0.00890  -0.0661   0.5752   1.0000
   4.750   0.8778   0.01762   0.00933  -0.0654   0.5634   1.0000
   5.000   0.9030   0.01794   0.00972  -0.0647   0.5516   1.0000
   5.250   0.9280   0.01822   0.01008  -0.0640   0.5388   1.0000
   5.500   0.9527   0.01847   0.01042  -0.0631   0.5245   1.0000
   5.750   0.9772   0.01874   0.01079  -0.0622   0.5097   1.0000
   6.000   1.0012   0.01893   0.01114  -0.0612   0.4925   1.0000
   6.250   1.0240   0.01882   0.01105  -0.0596   0.4675   1.0000
   6.500   1.0449   0.01859   0.01087  -0.0578   0.4354   1.0000
   6.750   1.0659   0.01852   0.01089  -0.0562   0.4035   1.0000
   7.000   1.0853   0.01850   0.01099  -0.0545   0.3577   1.0000
   7.250   1.1004   0.01904   0.01120  -0.0524   0.2622   1.0000
   7.750   1.1049   0.02496   0.01550  -0.0463   0.0729   1.0000
   8.000   1.1162   0.02675   0.01730  -0.0441   0.0607   1.0000
   8.250   1.1301   0.02826   0.01893  -0.0420   0.0544   1.0000
   8.500   1.1410   0.03027   0.02088  -0.0399   0.0507   1.0000
   8.750   1.1584   0.03224   0.02293  -0.0381   0.0486   1.0000
   9.000   1.1789   0.03432   0.02519  -0.0368   0.0462   1.0000
   9.250   1.1977   0.03632   0.02728  -0.0357   0.0430   1.0000
   9.500   1.2193   0.03919   0.03019  -0.0350   0.0410   1.0000
   9.750   1.2422   0.04302   0.03426  -0.0344   0.0405   1.0000
  10.000   1.2591   0.04656   0.03816  -0.0332   0.0405   1.0000
  10.250   1.2700   0.04989   0.04195  -0.0313   0.0410   1.0000
  10.500   1.2738   0.05363   0.04627  -0.0289   0.0421   1.0000
  10.750   1.2634   0.05807   0.05135  -0.0258   0.0436   1.0000
  11.000   1.2491   0.06239   0.05611  -0.0231   0.0448   1.0000
  11.250   1.2307   0.06632   0.06035  -0.0205   0.0456   1.0000
  11.500   1.2115   0.07043   0.06470  -0.0192   0.0463   1.0000
  11.750   1.1912   0.07500   0.06949  -0.0192   0.0469   1.0000
  12.000   1.1700   0.08015   0.07484  -0.0205   0.0474   1.0000
  12.250   1.1481   0.08596   0.08082  -0.0231   0.0478   1.0000
  12.500   1.1253   0.09254   0.08755  -0.0267   0.0482   1.0000
  12.750   1.1015   0.10006   0.09520  -0.0315   0.0485   1.0000
  13.000   1.0791   0.10820   0.10344  -0.0367   0.0490   1.0000
  13.250   0.9098   0.11566   0.11137  -0.0388   0.0482   1.0000
  13.500   0.8818   0.12381   0.11957  -0.0439   0.0492   1.0000
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