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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 50,000
Max Cl/Cd: 40.67 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe210-il-50000.txt
Download as CSV file: xf-goe210-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4028   0.12282   0.11576  -0.0129   1.0000   0.1086
  -9.250  -0.4065   0.12209   0.11512  -0.0157   1.0000   0.1109
  -9.000  -0.4141   0.12207   0.11523  -0.0190   1.0000   0.1116
  -8.750  -0.3871   0.11316   0.10623  -0.0155   1.0000   0.1176
  -8.500  -0.3840   0.11064   0.10378  -0.0167   1.0000   0.1223
  -8.250  -0.3902   0.10996   0.10323  -0.0194   1.0000   0.1250
  -8.000  -0.3866   0.10636   0.09972  -0.0200   1.0000   0.1272
  -7.750  -0.3725   0.10168   0.09504  -0.0186   1.0000   0.1340
  -7.500  -0.3766   0.10030   0.09379  -0.0208   1.0000   0.1386
  -7.250  -0.3767   0.09798   0.09159  -0.0242   1.0000   0.1411
  -7.000  -0.3642   0.09336   0.08699  -0.0209   1.0000   0.1490
  -6.750  -0.3674   0.09276   0.08649  -0.0277   1.0000   0.1543
  -6.500  -0.3564   0.08755   0.08135  -0.0227   1.0000   0.1611
  -6.250  -0.3562   0.08681   0.08067  -0.0300   1.0000   0.1690
  -6.000  -0.3479   0.08199   0.07595  -0.0241   1.0000   0.1785
  -5.250  -0.3341   0.07373   0.06787  -0.0260   1.0000   0.2151
  -5.000  -0.3293   0.07093   0.06513  -0.0248   1.0000   0.2305
  -4.750  -0.3246   0.06823   0.06250  -0.0233   1.0000   0.2472
  -4.500  -0.3186   0.06599   0.06028  -0.0246   1.0000   0.2715
  -4.250   0.0169   0.03868   0.03206  -0.0256   1.0000   1.0000
  -4.000   0.0279   0.03684   0.03029  -0.0265   1.0000   1.0000
  -3.750   0.0384   0.03510   0.02861  -0.0273   1.0000   1.0000
  -3.500   0.0398   0.03393   0.02755  -0.0259   1.0000   0.9965
  -3.250  -0.0135   0.03573   0.02962  -0.0119   1.0000   0.9671
  -3.000  -0.3297   0.05220   0.04713   0.0094   1.0000   0.5338
  -2.750  -0.3402   0.04991   0.04499   0.0210   1.0000   0.5946
  -2.500  -0.3478   0.04760   0.04280   0.0317   1.0000   0.6550
  -2.250  -0.3504   0.04531   0.04059   0.0391   1.0000   0.7059
  -2.000  -0.3460   0.04265   0.03799   0.0447   1.0000   0.7461
  -1.750  -0.0229   0.03435   0.02613  -0.0558   1.0000   0.2216
  -1.500   0.0187   0.03251   0.02346  -0.0580   1.0000   0.1811
  -1.250   0.0518   0.03097   0.02141  -0.0589   1.0000   0.1661
  -1.000   0.0811   0.02977   0.01987  -0.0594   1.0000   0.1655
  -0.750   0.1095   0.02879   0.01856  -0.0597   1.0000   0.1641
  -0.500   0.1371   0.02798   0.01745  -0.0599   1.0000   0.1621
  -0.250   0.1633   0.02740   0.01662  -0.0597   1.0000   0.1629
   0.000   0.1896   0.02712   0.01604  -0.0596   1.0000   0.1687
   0.250   0.2160   0.02673   0.01561  -0.0597   1.0000   0.1809
   0.500   0.2431   0.02647   0.01531  -0.0600   1.0000   0.1920
   0.750   0.2710   0.02633   0.01516  -0.0607   1.0000   0.2128
   1.000   0.2974   0.02392   0.01510  -0.0609   1.0000   0.9180
   1.250   0.3159   0.02465   0.01503  -0.0595   1.0000   1.0000
   1.500   0.3363   0.02549   0.01556  -0.0595   1.0000   1.0000
   1.750   0.3715   0.02654   0.01637  -0.0624   0.9936   1.0000
   2.000   0.4259   0.02769   0.01732  -0.0688   0.9749   1.0000
   2.250   0.4860   0.02875   0.01827  -0.0758   0.9557   1.0000
   2.500   0.5417   0.02934   0.01884  -0.0813   0.9292   1.0000
   2.750   0.6069   0.02935   0.01886  -0.0871   0.8993   1.0000
   3.000   0.6635   0.02899   0.01861  -0.0907   0.8712   1.0000
   3.250   0.7085   0.02873   0.01846  -0.0924   0.8457   1.0000
   3.500   0.7521   0.02829   0.01815  -0.0933   0.8213   1.0000
   3.750   0.7980   0.02743   0.01749  -0.0936   0.7972   1.0000
   4.000   0.8383   0.02652   0.01671  -0.0926   0.7704   1.0000
   4.250   0.8671   0.02596   0.01627  -0.0900   0.7362   1.0000
   4.500   0.8990   0.02503   0.01541  -0.0872   0.6994   1.0000
   4.750   0.9262   0.02435   0.01477  -0.0839   0.6552   1.0000
   5.000   0.9494   0.02409   0.01443  -0.0807   0.6034   1.0000
   5.250   0.9746   0.02404   0.01414  -0.0780   0.5558   1.0000
   5.500   0.9984   0.02455   0.01444  -0.0761   0.5140   1.0000
   5.750   1.0225   0.02538   0.01516  -0.0747   0.4807   1.0000
   6.000   1.0463   0.02630   0.01598  -0.0734   0.4521   1.0000
   6.250   1.0700   0.02724   0.01679  -0.0722   0.4257   1.0000
   6.500   1.0921   0.02826   0.01778  -0.0710   0.4002   1.0000
   6.750   1.1130   0.02930   0.01889  -0.0697   0.3750   1.0000
   7.000   1.1350   0.03043   0.02000  -0.0685   0.3520   1.0000
   7.250   1.1566   0.03175   0.02143  -0.0674   0.3307   1.0000
   7.500   1.1790   0.03331   0.02304  -0.0664   0.3098   1.0000
   7.750   1.1991   0.03511   0.02502  -0.0650   0.2872   1.0000
   8.000   1.2193   0.03733   0.02742  -0.0637   0.2659   1.0000
   8.250   1.2377   0.03988   0.03024  -0.0623   0.2482   1.0000
   8.500   1.2554   0.04237   0.03300  -0.0609   0.2334   1.0000
   8.750   1.2737   0.04387   0.03455  -0.0595   0.2155   1.0000
   9.000   1.2874   0.04511   0.03590  -0.0577   0.1958   1.0000
   9.250   1.2988   0.04678   0.03782  -0.0556   0.1772   1.0000
   9.500   1.3076   0.04734   0.03840  -0.0532   0.1520   1.0000
   9.750   1.3149   0.04877   0.03975  -0.0504   0.1278   1.0000
  10.000   1.3171   0.05208   0.04342  -0.0473   0.1129   1.0000
  10.250   1.3237   0.05489   0.04634  -0.0450   0.1020   1.0000
  10.500   1.3208   0.05862   0.05052  -0.0423   0.0958   1.0000
  10.750   1.3237   0.06183   0.05383  -0.0403   0.0901   1.0000
  11.000   1.3085   0.06657   0.05906  -0.0375   0.0888   1.0000
  11.250   1.2885   0.07112   0.06396  -0.0349   0.0884   1.0000
  11.500   1.2653   0.07590   0.06902  -0.0331   0.0887   1.0000
  11.750   1.2405   0.08125   0.07459  -0.0327   0.0893   1.0000
  12.000   1.2158   0.08725   0.08076  -0.0337   0.0901   1.0000
  12.250   1.1920   0.09392   0.08755  -0.0359   0.0909   1.0000
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