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GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
Reynolds number: 200,000
Max Cl/Cd: 61.06 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417a-il-200000-n5.txt
Download as CSV file: xf-goe417a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417A (GEW. PLATTE) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3606   0.10840   0.10480  -0.0148   1.0000   0.0207
  -8.000  -0.3661   0.10721   0.10365  -0.0132   1.0000   0.0208
  -7.750  -0.3732   0.10623   0.10272  -0.0115   1.0000   0.0208
  -7.250  -0.3537   0.09907   0.09557  -0.0139   0.9972   0.0210
  -7.000  -0.3354   0.09529   0.09178  -0.0172   0.9945   0.0213
  -6.750  -0.3167   0.09188   0.08836  -0.0210   0.9910   0.0216
  -6.500  -0.2975   0.08866   0.08512  -0.0248   0.9878   0.0219
  -6.250  -0.2751   0.08538   0.08182  -0.0293   0.9852   0.0223
  -6.000  -0.2553   0.08233   0.07876  -0.0329   0.9811   0.0228
  -5.750  -0.2299   0.07908   0.07546  -0.0378   0.9773   0.0233
  -5.500  -0.1976   0.07604   0.07237  -0.0442   0.9741   0.0241
  -5.250  -0.1687   0.07354   0.06981  -0.0496   0.9687   0.0243
  -5.000  -0.1316   0.07069   0.06688  -0.0567   0.9654   0.0244
  -4.750  -0.0991   0.06813   0.06424  -0.0623   0.9608   0.0245
  -4.500  -0.0643   0.06553   0.06153  -0.0678   0.9564   0.0245
  -4.250  -0.0434   0.06125   0.05727  -0.0695   0.9537   0.0247
  -4.000  -0.0283   0.05787   0.05391  -0.0697   0.9486   0.0250
  -3.750  -0.0039   0.05501   0.05103  -0.0720   0.9440   0.0255
  -3.500   0.0296   0.05225   0.04819  -0.0761   0.9412   0.0260
  -3.250   0.0555   0.04996   0.04586  -0.0781   0.9359   0.0265
  -3.000   0.0849   0.04764   0.04348  -0.0807   0.9312   0.0271
  -2.750   0.1201   0.04526   0.04101  -0.0844   0.9284   0.0277
  -2.500   0.1613   0.04311   0.03875  -0.0887   0.9264   0.0287
  -2.250   0.1911   0.04217   0.03766  -0.0896   0.9180   0.0292
  -2.000   0.2351   0.04100   0.03626  -0.0930   0.9147   0.0294
  -1.750   0.2640   0.03768   0.03293  -0.0951   0.9124   0.0297
  -1.500   0.2767   0.03546   0.03073  -0.0934   0.9030   0.0300
  -1.250   0.3063   0.03323   0.02846  -0.0950   0.8990   0.0305
  -1.000   0.3295   0.03159   0.02676  -0.0947   0.8903   0.0311
  -0.750   0.3616   0.02985   0.02494  -0.0960   0.8833   0.0318
  -0.500   0.3855   0.02847   0.02348  -0.0953   0.8715   0.0326
  -0.250   0.4172   0.02700   0.02190  -0.0960   0.8613   0.0338
   0.250   0.4863   0.02581   0.02027  -0.0964   0.8350   0.0364
   0.500   0.5129   0.02326   0.01767  -0.0969   0.8187   0.0373
   0.750   0.5456   0.02158   0.01592  -0.0985   0.7961   0.0391
   1.000   0.5862   0.02033   0.01446  -0.1009   0.7708   0.0415
   1.250   0.6259   0.02017   0.01391  -0.1020   0.7427   0.0453
   1.500   0.6568   0.01975   0.01315  -0.1018   0.7181   0.0461
   1.750   0.6796   0.01815   0.01145  -0.1013   0.6942   0.0475
   2.000   0.7031   0.01750   0.01067  -0.1004   0.6709   0.0496
   2.250   0.7271   0.01716   0.01015  -0.0992   0.6470   0.0533
   2.500   0.7510   0.01686   0.00962  -0.0978   0.6224   0.0578
   2.750   0.7727   0.01636   0.00899  -0.0966   0.5968   0.0606
   3.000   0.7951   0.01638   0.00875  -0.0949   0.5711   0.0690
   3.250   0.8158   0.01594   0.00821  -0.0935   0.5461   0.0755
   3.500   0.8376   0.01576   0.00790  -0.0922   0.5243   0.0892
   3.750   0.8601   0.01550   0.00751  -0.0909   0.5025   0.0980
   4.000   0.8879   0.01505   0.00670  -0.0893   0.4781   0.0389
   4.250   0.9093   0.01502   0.00645  -0.0876   0.4388   0.0373
   4.500   0.9267   0.01523   0.00636  -0.0854   0.3747   0.0370
   4.750   0.9416   0.01567   0.00638  -0.0830   0.2938   0.0371
   5.000   0.9592   0.01608   0.00653  -0.0812   0.2449   0.0381
   5.250   0.9792   0.01640   0.00676  -0.0798   0.2207   0.0409
   5.500   1.0007   0.01662   0.00693  -0.0786   0.2038   0.0422
   5.750   1.0278   0.01691   0.00718  -0.0788   0.1865   0.0429
   6.000   1.0526   0.01724   0.00742  -0.0784   0.1677   0.0439
   6.250   1.0751   0.01762   0.00769  -0.0775   0.1440   0.0454
   6.500   1.0879   0.01878   0.00827  -0.0751   0.0602   0.0486
   6.750   1.1048   0.01954   0.00897  -0.0731   0.0472   0.0548
   7.000   1.1226   0.02020   0.00964  -0.0712   0.0415   0.0624
   7.250   1.1350   0.02011   0.01033  -0.0682   0.0387   0.6625
   7.500   1.2505   0.02215   0.01293  -0.0890   0.0301   1.0000
   7.750   1.2650   0.02292   0.01376  -0.0866   0.0284   1.0000
   8.000   1.2782   0.02377   0.01465  -0.0840   0.0270   1.0000
   8.250   1.2892   0.02477   0.01568  -0.0811   0.0256   1.0000
   8.500   1.2980   0.02599   0.01692  -0.0778   0.0244   1.0000
   8.750   1.3112   0.02674   0.01779  -0.0753   0.0232   1.0000
   9.000   1.3216   0.02765   0.01878  -0.0722   0.0220   1.0000
   9.250   1.3309   0.02866   0.01986  -0.0691   0.0212   1.0000
   9.500   1.3400   0.02974   0.02101  -0.0660   0.0205   1.0000
   9.750   1.3491   0.03084   0.02216  -0.0630   0.0198   1.0000
  10.000   1.3580   0.03210   0.02348  -0.0602   0.0192   1.0000
  10.250   1.3672   0.03393   0.02534  -0.0577   0.0185   1.0000
  10.500   1.3778   0.03520   0.02678  -0.0551   0.0181   1.0000
  10.750   1.3868   0.03639   0.02816  -0.0524   0.0172   1.0000
  11.000   1.3953   0.03786   0.02979  -0.0498   0.0165   1.0000
  11.250   1.4023   0.03943   0.03154  -0.0471   0.0160   1.0000
  11.500   1.4083   0.04115   0.03344  -0.0444   0.0156   1.0000
  11.750   1.4125   0.04291   0.03537  -0.0417   0.0152   1.0000
  12.000   1.4153   0.04479   0.03741  -0.0390   0.0149   1.0000
  12.250   1.4164   0.04677   0.03955  -0.0364   0.0147   1.0000
  12.500   1.4158   0.04887   0.04180  -0.0339   0.0144   1.0000
  12.750   1.4137   0.05130   0.04440  -0.0315   0.0142   1.0000
  13.000   1.4095   0.05397   0.04724  -0.0292   0.0140   1.0000
  13.250   1.4026   0.05712   0.05059  -0.0272   0.0139   1.0000
  13.500   1.3931   0.06064   0.05435  -0.0255   0.0138   1.0000
  13.750   1.3802   0.06458   0.05852  -0.0243   0.0137   1.0000
  14.000   1.3665   0.06873   0.06292  -0.0237   0.0137   1.0000
  14.250   1.3492   0.07368   0.06813  -0.0239   0.0136   1.0000
  14.500   1.3313   0.07902   0.07372  -0.0249   0.0135   1.0000
  14.750   1.3142   0.08465   0.07956  -0.0266   0.0135   1.0000
  15.000   1.2939   0.09128   0.08643  -0.0294   0.0134   1.0000
  15.250   1.2737   0.09846   0.09381  -0.0327   0.0134   1.0000
  15.500   1.2538   0.10613   0.10166  -0.0368   0.0134   1.0000
  15.750   1.2344   0.11414   0.10980  -0.0412   0.0136   1.0000
  16.000   1.2143   0.12297   0.11878  -0.0464   0.0136   1.0000
  16.250   1.1931   0.13298   0.12894  -0.0526   0.0137   1.0000
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