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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 500,000
Max Cl/Cd: 105.13 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe210-il-500000.txt
Download as CSV file: xf-goe210-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 210 (DAIMLER) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3590   0.08450   0.08240  -0.0217   1.0000   0.0150
  -7.000  -0.3571   0.08185   0.07979  -0.0226   1.0000   0.0155
  -6.750  -0.3558   0.07923   0.07720  -0.0233   1.0000   0.0160
  -6.500  -0.3537   0.07657   0.07458  -0.0245   1.0000   0.0168
  -6.250  -0.3138   0.07096   0.06890  -0.0387   0.9969   0.0177
  -6.000  -0.2750   0.06529   0.06315  -0.0484   0.9937   0.0178
  -5.750  -0.2381   0.05977   0.05754  -0.0564   0.9893   0.0178
  -5.500  -0.2104   0.05277   0.05048  -0.0633   0.9857   0.0183
  -5.250  -0.1780   0.04914   0.04679  -0.0681   0.9834   0.0188
  -5.000  -0.1449   0.04550   0.04307  -0.0728   0.9777   0.0196
  -4.750  -0.1057   0.04138   0.03881  -0.0785   0.9732   0.0212
  -4.500  -0.0554   0.03734   0.03444  -0.0838   0.9681   0.0238
  -4.250  -0.0214   0.03348   0.03031  -0.0863   0.9589   0.0240
  -4.000   0.0038   0.02759   0.02419  -0.0892   0.9476   0.0253
  -3.750   0.0308   0.02564   0.02210  -0.0900   0.9349   0.0263
  -3.500   0.0583   0.02368   0.01995  -0.0904   0.9202   0.0282
  -3.250   0.0901   0.02317   0.01910  -0.0895   0.9045   0.0325
  -3.000   0.1160   0.01815   0.01355  -0.0901   0.8890   0.0344
  -2.750   0.1412   0.01750   0.01285  -0.0900   0.8728   0.0374
  -2.500   0.1700   0.01840   0.01343  -0.0890   0.8565   0.0439
  -2.250   0.1982   0.01284   0.00717  -0.0887   0.8441   0.0350
  -2.000   0.2249   0.01245   0.00671  -0.0885   0.8309   0.0385
  -1.750   0.2525   0.01127   0.00526  -0.0880   0.8187   0.0380
  -1.500   0.2794   0.01057   0.00439  -0.0874   0.8044   0.0385
  -1.250   0.3062   0.01017   0.00386  -0.0870   0.7899   0.0407
  -1.000   0.3334   0.00971   0.00331  -0.0866   0.7783   0.0416
  -0.750   0.3607   0.00937   0.00288  -0.0863   0.7695   0.0423
  -0.500   0.3882   0.00907   0.00254  -0.0861   0.7596   0.0430
  -0.250   0.4157   0.00887   0.00229  -0.0859   0.7496   0.0442
   0.000   0.4432   0.00859   0.00193  -0.0857   0.7399   0.0461
   0.250   0.4709   0.00843   0.00174  -0.0855   0.7295   0.0490
   0.500   0.4987   0.00834   0.00164  -0.0853   0.7203   0.0527
   0.750   0.5263   0.00829   0.00157  -0.0852   0.7107   0.0609
   1.000   0.5527   0.00726   0.00166  -0.0855   0.6994   0.5149
   1.250   0.5774   0.00618   0.00165  -0.0845   0.6848   1.0000
   1.500   0.6045   0.00627   0.00164  -0.0842   0.6680   1.0000
   1.750   0.6316   0.00635   0.00164  -0.0839   0.6504   1.0000
   2.000   0.6587   0.00646   0.00166  -0.0836   0.6322   1.0000
   2.250   0.6855   0.00659   0.00168  -0.0833   0.6103   1.0000
   2.500   0.7117   0.00677   0.00173  -0.0829   0.5766   1.0000
   2.750   0.7369   0.00708   0.00181  -0.0824   0.5271   1.0000
   3.000   0.7611   0.00753   0.00195  -0.0818   0.4642   1.0000
   3.250   0.7849   0.00809   0.00218  -0.0811   0.3979   1.0000
   3.500   0.8090   0.00863   0.00245  -0.0806   0.3416   1.0000
   3.750   0.8336   0.00912   0.00271  -0.0802   0.2952   1.0000
   4.000   0.8583   0.00958   0.00296  -0.0798   0.2554   1.0000
   4.250   0.8834   0.00999   0.00321  -0.0794   0.2266   1.0000
   4.500   0.9090   0.01031   0.00346  -0.0791   0.2092   1.0000
   4.750   0.9347   0.01062   0.00371  -0.0788   0.1977   1.0000
   5.000   0.9606   0.01089   0.00396  -0.0785   0.1882   1.0000
   5.250   0.9864   0.01116   0.00422  -0.0783   0.1800   1.0000
   5.500   1.0118   0.01148   0.00451  -0.0779   0.1698   1.0000
   5.750   1.0374   0.01177   0.00477  -0.0776   0.1589   1.0000
   6.000   1.0629   0.01204   0.00503  -0.0773   0.1464   1.0000
   6.250   1.0881   0.01237   0.00531  -0.0770   0.1302   1.0000
   6.500   1.1103   0.01307   0.00574  -0.0763   0.0830   1.0000
   6.750   1.1330   0.01370   0.00627  -0.0756   0.0689   1.0000
   7.000   1.1573   0.01410   0.00671  -0.0751   0.0643   1.0000
   7.250   1.1807   0.01460   0.00721  -0.0746   0.0590   1.0000
   7.500   1.2050   0.01498   0.00764  -0.0741   0.0534   1.0000
   7.750   1.2281   0.01550   0.00814  -0.0735   0.0439   1.0000
   8.000   1.2500   0.01616   0.00864  -0.0727   0.0222   1.0000
   8.250   1.2709   0.01697   0.00948  -0.0716   0.0171   1.0000
   8.500   1.2914   0.01782   0.01042  -0.0705   0.0151   1.0000
   8.750   1.3107   0.01880   0.01157  -0.0692   0.0135   1.0000
   9.000   1.3305   0.01963   0.01252  -0.0680   0.0129   1.0000
   9.250   1.3486   0.02061   0.01362  -0.0667   0.0123   1.0000
   9.500   1.3653   0.02169   0.01482  -0.0651   0.0117   1.0000
   9.750   1.3800   0.02289   0.01613  -0.0633   0.0112   1.0000
  10.000   1.3926   0.02422   0.01758  -0.0613   0.0108   1.0000
  10.250   1.4021   0.02575   0.01923  -0.0589   0.0104   1.0000
  10.500   1.4079   0.02747   0.02107  -0.0561   0.0101   1.0000
  10.750   1.4070   0.02960   0.02332  -0.0524   0.0098   1.0000
  11.000   1.4025   0.03249   0.02638  -0.0486   0.0094   1.0000
  11.250   1.4101   0.03377   0.02781  -0.0465   0.0092   1.0000
  11.500   1.4168   0.03520   0.02940  -0.0445   0.0089   1.0000
  11.750   1.4200   0.03715   0.03150  -0.0424   0.0088   1.0000
  12.000   1.4216   0.03937   0.03389  -0.0404   0.0087   1.0000
  12.250   1.4217   0.04183   0.03651  -0.0387   0.0086   1.0000
  12.500   1.4203   0.04456   0.03942  -0.0373   0.0085   1.0000
  12.750   1.4171   0.04759   0.04263  -0.0362   0.0084   1.0000
  13.000   1.4122   0.05094   0.04619  -0.0355   0.0083   1.0000
  13.250   1.4053   0.05466   0.05010  -0.0351   0.0082   1.0000
  13.500   1.3967   0.05875   0.05438  -0.0352   0.0082   1.0000
  13.750   1.3857   0.06334   0.05917  -0.0358   0.0082   1.0000
  14.000   1.3735   0.06835   0.06437  -0.0369   0.0082   1.0000
  14.250   1.3593   0.07389   0.07009  -0.0386   0.0082   1.0000
  14.500   1.3438   0.07999   0.07639  -0.0410   0.0082   1.0000
  14.750   1.3275   0.08666   0.08323  -0.0441   0.0082   1.0000
  15.000   1.3102   0.09397   0.09073  -0.0478   0.0082   1.0000
  15.250   1.2927   0.10183   0.09875  -0.0522   0.0083   1.0000
  15.500   1.2744   0.11022   0.10730  -0.0569   0.0084   1.0000
  15.750   1.2566   0.11887   0.11610  -0.0620   0.0084   1.0000
  16.000   1.2379   0.12803   0.12540  -0.0674   0.0085   1.0000
  16.250   1.2195   0.13745   0.13495  -0.0730   0.0086   1.0000
  16.500   1.2008   0.14727   0.14487  -0.0789   0.0087   1.0000
  16.750   1.1818   0.15767   0.15538  -0.0852   0.0089   1.0000
  17.000   1.1608   0.16920   0.16700  -0.0921   0.0091   1.0000
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