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GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
Reynolds number: 500,000
Max Cl/Cd: 68.11 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417a-il-500000-n5.txt
Download as CSV file: xf-goe417a-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3918   0.12889   0.12649  -0.0171   1.0000   0.0094
 -11.000  -0.3892   0.12659   0.12421  -0.0169   1.0000   0.0095
 -10.750  -0.3874   0.12417   0.12181  -0.0166   1.0000   0.0095
 -10.500  -0.3821   0.12307   0.12071  -0.0161   1.0000   0.0104
 -10.250  -0.3724   0.11997   0.11761  -0.0180   0.9994   0.0113
 -10.000  -0.3626   0.11646   0.11410  -0.0203   0.9985   0.0115
  -9.750  -0.3520   0.11318   0.11081  -0.0227   0.9974   0.0114
  -9.500  -0.3410   0.10982   0.10746  -0.0252   0.9960   0.0121
  -9.250  -0.3289   0.10698   0.10462  -0.0276   0.9948   0.0124
  -9.000  -0.3177   0.10401   0.10165  -0.0298   0.9935   0.0125
  -8.750  -0.3075   0.10121   0.09885  -0.0318   0.9917   0.0127
  -8.500  -0.2956   0.09853   0.09617  -0.0340   0.9897   0.0141
  -8.250  -0.2833   0.09541   0.09305  -0.0369   0.9876   0.0139
  -8.000  -0.2659   0.09305   0.09068  -0.0401   0.9858   0.0171
  -7.750  -0.2528   0.08991   0.08753  -0.0433   0.9824   0.0172
  -7.500  -0.2375   0.08660   0.08421  -0.0468   0.9785   0.0173
  -7.250  -0.2143   0.08281   0.08040  -0.0529   0.9760   0.0175
  -6.750  -0.1801   0.07694   0.07452  -0.0585   0.9702   0.0181
  -6.500  -0.1593   0.07420   0.07177  -0.0621   0.9676   0.0191
  -6.250  -0.1331   0.07101   0.06854  -0.0671   0.9657   0.0200
  -6.000  -0.1017   0.06765   0.06513  -0.0735   0.9641   0.0202
  -5.750  -0.0743   0.06516   0.06258  -0.0787   0.9593   0.0203
  -5.500  -0.0439   0.06241   0.05977  -0.0841   0.9565   0.0204
  -5.250  -0.0080   0.05958   0.05687  -0.0904   0.9545   0.0204
  -5.000   0.0276   0.05659   0.05381  -0.0961   0.9530   0.0204
  -4.750   0.0423   0.05336   0.05059  -0.0961   0.9492   0.0205
  -4.500   0.0614   0.05067   0.04788  -0.0971   0.9449   0.0206
  -4.250   0.0878   0.04803   0.04520  -0.0998   0.9420   0.0207
  -4.000   0.1184   0.04555   0.04267  -0.1033   0.9397   0.0209
  -3.750   0.1378   0.04371   0.04081  -0.1038   0.9338   0.0211
  -3.500   0.1654   0.04164   0.03869  -0.1059   0.9300   0.0215
  -3.250   0.1967   0.03952   0.03650  -0.1087   0.9270   0.0219
  -3.000   0.2194   0.03780   0.03472  -0.1092   0.9200   0.0222
  -2.750   0.2504   0.03588   0.03273  -0.1113   0.9137   0.0227
  -2.500   0.2765   0.03439   0.03116  -0.1119   0.9056   0.0231
  -2.250   0.3069   0.03272   0.02941  -0.1134   0.8987   0.0233
  -2.000   0.3320   0.03127   0.02787  -0.1135   0.8904   0.0233
  -1.750   0.3613   0.02973   0.02623  -0.1144   0.8815   0.0234
  -1.500   0.3871   0.02834   0.02474  -0.1144   0.8687   0.0234
  -1.250   0.4151   0.02697   0.02324  -0.1146   0.8517   0.0234
  -1.000   0.4422   0.02568   0.02177  -0.1146   0.8226   0.0235
  -0.750   0.4680   0.02456   0.02034  -0.1140   0.7750   0.0235
  -0.500   0.4899   0.02364   0.01912  -0.1126   0.7379   0.0235
  -0.250   0.5119   0.02272   0.01797  -0.1111   0.7130   0.0236
   0.000   0.5339   0.02185   0.01687  -0.1096   0.6887   0.0236
   0.250   0.5552   0.02103   0.01586  -0.1081   0.6652   0.0236
   0.500   0.5744   0.01965   0.01432  -0.1066   0.6418   0.0238
   0.750   0.5924   0.01863   0.01317  -0.1051   0.6154   0.0240
   1.000   0.6107   0.01799   0.01237  -0.1035   0.5857   0.0245
   1.250   0.6311   0.01745   0.01167  -0.1020   0.5613   0.0249
   1.500   0.6528   0.01692   0.01097  -0.1005   0.5422   0.0253
   1.750   0.6748   0.01642   0.01031  -0.0991   0.5237   0.0255
   2.000   0.6973   0.01595   0.00970  -0.0978   0.5065   0.0258
   2.250   0.7202   0.01552   0.00913  -0.0965   0.4908   0.0262
   2.500   0.7427   0.01522   0.00866  -0.0950   0.4683   0.0269
   2.750   0.7651   0.01521   0.00843  -0.0934   0.4356   0.0276
   3.000   0.7851   0.01523   0.00814  -0.0915   0.3822   0.0277
   3.250   0.8020   0.01545   0.00791  -0.0892   0.3005   0.0278
   3.500   0.8193   0.01573   0.00775  -0.0871   0.2284   0.0279
   3.750   0.8412   0.01560   0.00745  -0.0858   0.2073   0.0279
   4.000   0.8639   0.01541   0.00712  -0.0846   0.1938   0.0280
   6.000   1.0363   0.01552   0.00645  -0.0749   0.0372   0.0407
   6.250   1.0575   0.01564   0.00658  -0.0734   0.0341   0.0321
   6.500   1.0775   0.01582   0.00678  -0.0718   0.0316   0.0304
   6.750   1.0967   0.01613   0.00711  -0.0700   0.0290   0.0292
   7.000   1.1161   0.01642   0.00745  -0.0684   0.0279   0.0286
   7.250   1.1355   0.01668   0.00776  -0.0667   0.0272   0.0284
   7.500   1.1543   0.01697   0.00812  -0.0650   0.0263   0.0283
   7.750   1.1719   0.01726   0.00848  -0.0630   0.0253   0.0286
   8.000   1.1887   0.01758   0.00885  -0.0609   0.0243   0.0293
   8.250   1.2050   0.01794   0.00923  -0.0587   0.0232   0.0309
   8.500   1.2204   0.01840   0.00972  -0.0564   0.0222   0.0338
   8.750   1.2339   0.01900   0.01035  -0.0538   0.0213   0.0350
   9.000   1.2435   0.01987   0.01131  -0.0505   0.0204   0.0355
   9.250   1.2588   0.02035   0.01185  -0.0483   0.0201   0.0361
   9.500   1.2735   0.02086   0.01243  -0.0461   0.0196   0.0379
   9.750   1.2876   0.02139   0.01308  -0.0438   0.0191   0.1178
  10.000   1.4528   0.02269   0.01556  -0.0762   0.0158   1.0000
  10.250   1.4586   0.02351   0.01642  -0.0724   0.0151   1.0000
  10.500   1.4678   0.02416   0.01715  -0.0692   0.0147   1.0000
  10.750   1.4780   0.02478   0.01786  -0.0662   0.0143   1.0000
  11.000   1.4897   0.02532   0.01849  -0.0636   0.0136   1.0000
  11.250   1.5005   0.02594   0.01918  -0.0610   0.0129   1.0000
  11.500   1.5121   0.02651   0.01980  -0.0585   0.0122   1.0000
  11.750   1.5225   0.02719   0.02053  -0.0560   0.0117   1.0000
  12.000   1.5314   0.02799   0.02138  -0.0533   0.0112   1.0000
  12.250   1.5362   0.02913   0.02259  -0.0503   0.0106   1.0000
  12.500   1.5425   0.03020   0.02378  -0.0475   0.0104   1.0000
  12.750   1.5486   0.03131   0.02502  -0.0448   0.0099   1.0000
  13.000   1.5553   0.03241   0.02623  -0.0424   0.0094   1.0000
  13.250   1.5599   0.03372   0.02765  -0.0398   0.0090   1.0000
  13.500   1.5668   0.03486   0.02887  -0.0377   0.0084   1.0000
  13.750   1.5708   0.03630   0.03040  -0.0355   0.0082   1.0000
  14.000   1.5737   0.03791   0.03210  -0.0334   0.0079   1.0000
  14.250   1.5736   0.03986   0.03414  -0.0314   0.0074   1.0000
  14.500   1.5720   0.04210   0.03651  -0.0295   0.0071   1.0000
  14.750   1.5718   0.04429   0.03885  -0.0280   0.0069   1.0000
  15.000   1.5671   0.04713   0.04184  -0.0267   0.0068   1.0000
  15.250   1.5633   0.05003   0.04489  -0.0257   0.0066   1.0000
  15.500   1.5581   0.05323   0.04824  -0.0251   0.0064   1.0000
  15.750   1.5517   0.05677   0.05193  -0.0249   0.0062   1.0000
  16.000   1.5457   0.06046   0.05576  -0.0250   0.0060   1.0000
  16.250   1.5416   0.06401   0.05943  -0.0254   0.0059   1.0000
  16.500   1.5295   0.06894   0.06454  -0.0264   0.0059   1.0000
  16.750   1.5214   0.07348   0.06921  -0.0276   0.0057   1.0000
  17.000   1.5120   0.07837   0.07422  -0.0290   0.0055   1.0000
  17.250   1.4953   0.08463   0.08064  -0.0312   0.0055   1.0000
  17.500   1.4801   0.09086   0.08703  -0.0336   0.0055   1.0000
  17.750   1.4626   0.09774   0.09405  -0.0364   0.0054   1.0000
  18.000   1.4418   0.10554   0.10202  -0.0399   0.0054   1.0000
  18.250   1.4230   0.11328   0.10990  -0.0436   0.0053   1.0000
  18.500   1.4048   0.12108   0.11784  -0.0473   0.0053   1.0000
  18.750   1.3822   0.13007   0.12699  -0.0519   0.0054   1.0000
  19.000   1.3600   0.13929   0.13635  -0.0567   0.0054   1.0000
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