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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 200,000
Max Cl/Cd: 79.1 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe300-il-200000.txt
Download as CSV file: xf-goe300-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2534   0.09695   0.09369  -0.0284   1.0000   0.0425
  -7.750  -0.2708   0.09668   0.09352  -0.0250   1.0000   0.0430
  -7.500  -0.2918   0.09678   0.09373  -0.0216   0.9990   0.0432
  -7.250  -0.2571   0.09153   0.08844  -0.0391   0.9884   0.0439
  -7.000  -0.2385   0.08673   0.08366  -0.0366   0.9863   0.0447
  -6.750  -0.2105   0.08254   0.07945  -0.0417   0.9817   0.0459
  -6.500  -0.1808   0.07838   0.07525  -0.0486   0.9744   0.0475
  -6.250  -0.1269   0.07391   0.07063  -0.0681   0.9649   0.0508
  -6.000  -0.0936   0.06836   0.06500  -0.0759   0.9582   0.0514
  -5.750  -0.0755   0.06451   0.06121  -0.0748   0.9527   0.0524
  -5.500  -0.0499   0.06137   0.05804  -0.0775   0.9432   0.0544
  -5.250  -0.0200   0.05807   0.05465  -0.0823   0.9318   0.0573
  -5.000   0.0289   0.05407   0.05027  -0.0936   0.9191   0.0601
  -4.750   0.0423   0.05061   0.04687  -0.0922   0.9081   0.0610
  -4.500   0.0582   0.04834   0.04458  -0.0912   0.8940   0.0628
  -4.250   0.0813   0.04606   0.04218  -0.0921   0.8796   0.0661
  -4.000   0.1233   0.04311   0.03874  -0.0973   0.8654   0.0708
  -3.750   0.1385   0.04025   0.03591  -0.0962   0.8512   0.0720
  -3.500   0.1583   0.03834   0.03394  -0.0956   0.8372   0.0748
  -3.250   0.2001   0.03724   0.03220  -0.0981   0.8235   0.0828
  -3.000   0.2173   0.03382   0.02881  -0.0977   0.8095   0.0843
  -2.750   0.2385   0.03208   0.02703  -0.0972   0.7943   0.0874
  -2.500   0.2740   0.03098   0.02539  -0.0981   0.7801   0.0968
  -2.250   0.2952   0.02859   0.02301  -0.0980   0.7667   0.0989
  -2.000   0.3202   0.02733   0.02163  -0.0978   0.7542   0.1047
  -1.750   0.3501   0.02588   0.01982  -0.0981   0.7430   0.1126
  -1.500   0.3752   0.02464   0.01849  -0.0980   0.7311   0.1178
  -1.250   0.4035   0.02353   0.01713  -0.0980   0.7193   0.1279
  -1.000   0.4325   0.02304   0.01631  -0.0979   0.7086   0.1402
  -0.750   0.4573   0.02159   0.01484  -0.0978   0.6980   0.1455
  -0.500   0.4843   0.02077   0.01388  -0.0977   0.6868   0.1591
  -0.250   0.4203   0.03068   0.02628  -0.0862   0.6903   0.1372
   0.000   0.5380   0.01931   0.01215  -0.0974   0.6670   0.1909
   0.250   0.5744   0.01778   0.00993  -0.0966   0.6580   0.1205
   0.500   0.6034   0.01683   0.00863  -0.0961   0.6492   0.1128
   0.750   0.6305   0.01640   0.00816  -0.0959   0.6391   0.1151
   1.000   0.6582   0.01597   0.00757  -0.0955   0.6304   0.1153
   1.250   0.6854   0.01559   0.00711  -0.0951   0.6198   0.1159
   1.500   0.7125   0.01531   0.00674  -0.0947   0.6092   0.1175
   1.750   0.7394   0.01516   0.00646  -0.0942   0.5989   0.1214
   2.000   0.7661   0.01503   0.00627  -0.0937   0.5869   0.1242
   2.250   0.7923   0.01468   0.00596  -0.0933   0.5756   0.1274
   2.500   0.8187   0.01456   0.00580  -0.0929   0.5648   0.1318
   2.750   0.8450   0.01451   0.00572  -0.0924   0.5532   0.1380
   3.000   0.8708   0.01437   0.00566  -0.0920   0.5414   0.1463
   3.250   0.8969   0.01433   0.00561  -0.0915   0.5304   0.1554
   3.500   0.9229   0.01432   0.00558  -0.0911   0.5196   0.1684
   3.750   0.9487   0.01428   0.00563  -0.0907   0.5075   0.1937
   4.000   0.9761   0.01298   0.00572  -0.0905   0.4959   1.0000
   4.250   1.0019   0.01322   0.00578  -0.0900   0.4850   1.0000
   4.500   1.0275   0.01343   0.00594  -0.0895   0.4737   1.0000
   4.750   1.0531   0.01367   0.00615  -0.0891   0.4632   1.0000
   5.250   1.1042   0.01417   0.00656  -0.0882   0.4442   1.0000
   5.500   1.1295   0.01444   0.00678  -0.0877   0.4350   1.0000
   5.750   1.1547   0.01470   0.00703  -0.0873   0.4261   1.0000
   6.000   1.1797   0.01497   0.00730  -0.0868   0.4171   1.0000
   6.250   1.2046   0.01527   0.00754  -0.0863   0.4086   1.0000
   6.500   1.2292   0.01554   0.00789  -0.0858   0.3996   1.0000
   6.750   1.2538   0.01589   0.00817  -0.0853   0.3918   1.0000
   7.000   1.2779   0.01618   0.00854  -0.0848   0.3824   1.0000
   7.250   1.3016   0.01654   0.00890  -0.0841   0.3733   1.0000
   7.500   1.3248   0.01690   0.00925  -0.0834   0.3632   1.0000
   7.750   1.3476   0.01725   0.00968  -0.0827   0.3525   1.0000
   8.000   1.3696   0.01767   0.01010  -0.0819   0.3411   1.0000
   8.250   1.3908   0.01814   0.01055  -0.0809   0.3287   1.0000
   8.500   1.4109   0.01861   0.01103  -0.0798   0.3147   1.0000
   8.750   1.4299   0.01910   0.01155  -0.0785   0.2989   1.0000
   9.000   1.4479   0.01963   0.01213  -0.0771   0.2816   1.0000
   9.250   1.4653   0.02019   0.01273  -0.0757   0.2640   1.0000
   9.500   1.4818   0.02080   0.01335  -0.0741   0.2476   1.0000
   9.750   1.4971   0.02147   0.01400  -0.0725   0.2326   1.0000
  10.000   1.5110   0.02222   0.01473  -0.0707   0.2195   1.0000
  10.250   1.5221   0.02308   0.01553  -0.0685   0.2090   1.0000
  10.500   1.5331   0.02393   0.01641  -0.0663   0.1997   1.0000
  10.750   1.5427   0.02492   0.01741  -0.0641   0.1915   1.0000
  11.000   1.5506   0.02606   0.01852  -0.0618   0.1839   1.0000
  11.250   1.5603   0.02716   0.01969  -0.0599   0.1772   1.0000
  11.500   1.5677   0.02842   0.02097  -0.0579   0.1705   1.0000
  11.750   1.5757   0.02971   0.02232  -0.0561   0.1642   1.0000
  12.000   1.5834   0.03100   0.02372  -0.0544   0.1580   1.0000
  12.250   1.5891   0.03258   0.02526  -0.0526   0.1522   1.0000
  12.500   1.5964   0.03393   0.02684  -0.0513   0.1462   1.0000
  12.750   1.6002   0.03566   0.02863  -0.0499   0.1402   1.0000
  13.000   1.6054   0.03735   0.03051  -0.0489   0.1335   1.0000
  13.250   1.6074   0.03942   0.03268  -0.0480   0.1260   1.0000
  13.500   1.6116   0.04148   0.03493  -0.0476   0.1158   1.0000
  13.750   1.6111   0.04417   0.03769  -0.0473   0.1020   1.0000
  14.000   1.6027   0.04787   0.04137  -0.0471   0.0843   1.0000
  14.250   1.5876   0.05246   0.04589  -0.0470   0.0698   1.0000
  14.500   1.5717   0.05731   0.05073  -0.0470   0.0607   1.0000
  14.750   1.5556   0.06239   0.05583  -0.0474   0.0552   1.0000
  15.000   1.5426   0.06722   0.06075  -0.0479   0.0508   1.0000
  15.250   1.5263   0.07266   0.06625  -0.0488   0.0482   1.0000
  15.500   1.5152   0.07750   0.07120  -0.0496   0.0457   1.0000
  15.750   1.5039   0.08247   0.07629  -0.0506   0.0436   1.0000
  16.000   1.4914   0.08773   0.08163  -0.0518   0.0420   1.0000
  16.250   1.4775   0.09321   0.08715  -0.0531   0.0407   1.0000
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