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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 100,000
Max Cl/Cd: 56.99 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe282-il-100000.txt
Download as CSV file: xf-goe282-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 282 (DAIMLER XIII) AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3422   0.09985   0.09541  -0.0239   1.0000   0.0902
  -7.250  -0.3603   0.09941   0.09508  -0.0258   1.0000   0.0912
  -7.000  -0.3697   0.09840   0.09411  -0.0331   1.0000   0.0918
  -6.750  -0.3557   0.09233   0.08811  -0.0208   1.0000   0.0949
  -6.500  -0.3551   0.09000   0.08583  -0.0192   1.0000   0.0979
  -6.250  -0.3569   0.08776   0.08364  -0.0197   1.0000   0.1013
  -6.000  -0.3524   0.08604   0.08184  -0.0346   1.0000   0.1055
  -5.750  -0.3533   0.08181   0.07773  -0.0276   1.0000   0.1067
  -5.500  -0.3508   0.07910   0.07508  -0.0237   1.0000   0.1089
  -5.250  -0.3454   0.07662   0.07262  -0.0231   1.0000   0.1125
  -5.000  -0.3219   0.07290   0.06872  -0.0351   1.0000   0.1202
  -4.750  -0.3221   0.07011   0.06605  -0.0299   1.0000   0.1224
  -4.500  -0.3138   0.06787   0.06383  -0.0289   1.0000   0.1277
  -4.250  -0.2794   0.06344   0.05922  -0.0379   0.9980   0.1363
  -4.000  -0.2399   0.05956   0.05527  -0.0429   0.9918   0.1441
  -3.750  -0.1914   0.05499   0.05050  -0.0513   0.9852   0.1548
  -3.500  -0.1411   0.05081   0.04607  -0.0598   0.9778   0.1676
  -3.250  -0.0864   0.04698   0.04192  -0.0683   0.9717   0.1811
  -3.000  -0.0090   0.03557   0.02923  -0.0811   0.9704   0.1092
  -2.750   0.0422   0.03062   0.02330  -0.0862   0.9644   0.1040
  -2.500   0.0923   0.02822   0.02043  -0.0909   0.9589   0.1079
  -2.250   0.1360   0.02666   0.01860  -0.0941   0.9500   0.1115
  -2.000   0.1872   0.02512   0.01656  -0.0983   0.9439   0.1200
  -1.750   0.2280   0.02433   0.01574  -0.1007   0.9330   0.1313
  -1.500   0.2742   0.02329   0.01453  -0.1039   0.9246   0.1493
  -1.250   0.3206   0.02251   0.01383  -0.1072   0.9159   0.1930
  -1.000   0.3612   0.02185   0.01322  -0.1096   0.9047   0.2358
  -0.750   0.4129   0.02099   0.01241  -0.1139   0.8992   0.2719
  -0.500   0.4496   0.02032   0.01185  -0.1153   0.8865   0.3034
  -0.250   0.4871   0.01953   0.01111  -0.1164   0.8738   0.3234
   0.000   0.5247   0.01864   0.01026  -0.1172   0.8602   0.3438
   0.250   0.5612   0.01766   0.00941  -0.1177   0.8450   0.3747
   0.500   0.5907   0.01546   0.00876  -0.1164   0.8292   1.0000
   0.750   0.6241   0.01518   0.00814  -0.1162   0.8128   1.0000
   1.000   0.6557   0.01502   0.00773  -0.1160   0.7968   1.0000
   1.250   0.6852   0.01497   0.00748  -0.1156   0.7796   1.0000
   1.500   0.7137   0.01501   0.00735  -0.1152   0.7619   1.0000
   1.750   0.7421   0.01509   0.00728  -0.1147   0.7448   1.0000
   2.000   0.7702   0.01523   0.00727  -0.1143   0.7279   1.0000
   2.250   0.7978   0.01542   0.00732  -0.1138   0.7109   1.0000
   2.500   0.8251   0.01564   0.00740  -0.1132   0.6940   1.0000
   2.750   0.8520   0.01588   0.00751  -0.1127   0.6772   1.0000
   3.000   0.8777   0.01615   0.00771  -0.1120   0.6596   1.0000
   3.250   0.9032   0.01643   0.00794  -0.1113   0.6419   1.0000
   3.500   0.9288   0.01671   0.00815  -0.1105   0.6241   1.0000
   3.750   0.9544   0.01700   0.00835  -0.1098   0.6061   1.0000
   4.000   0.9802   0.01730   0.00855  -0.1091   0.5878   1.0000
   4.250   1.0045   0.01766   0.00887  -0.1082   0.5672   1.0000
   4.500   1.0292   0.01806   0.00917  -0.1073   0.5465   1.0000
   4.750   1.0543   0.01854   0.00951  -0.1065   0.5266   1.0000
   5.000   1.0777   0.01906   0.01004  -0.1056   0.5048   1.0000
   5.250   1.1018   0.01957   0.01046  -0.1048   0.4847   1.0000
   5.500   1.1256   0.02006   0.01086  -0.1039   0.4654   1.0000
   5.750   1.1479   0.02049   0.01131  -0.1028   0.4458   1.0000
   6.000   1.1707   0.02089   0.01172  -0.1018   0.4282   1.0000
   6.250   1.1938   0.02132   0.01215  -0.1009   0.4127   1.0000
   6.500   1.2169   0.02179   0.01263  -0.1000   0.3987   1.0000
   6.750   1.2385   0.02216   0.01299  -0.0989   0.3830   1.0000
   7.000   1.2582   0.02243   0.01324  -0.0974   0.3647   1.0000
   7.250   1.2765   0.02278   0.01357  -0.0958   0.3456   1.0000
   7.500   1.2952   0.02321   0.01404  -0.0943   0.3283   1.0000
   7.750   1.3143   0.02372   0.01458  -0.0929   0.3131   1.0000
   8.000   1.3341   0.02428   0.01521  -0.0916   0.3006   1.0000
   8.250   1.3507   0.02480   0.01578  -0.0899   0.2838   1.0000
   8.500   1.3664   0.02537   0.01639  -0.0881   0.2670   1.0000
   8.750   1.3822   0.02598   0.01706  -0.0863   0.2517   1.0000
   9.000   1.3983   0.02663   0.01780  -0.0845   0.2386   1.0000
   9.250   1.4137   0.02731   0.01860  -0.0827   0.2261   1.0000
   9.500   1.4278   0.02803   0.01941  -0.0807   0.2129   1.0000
   9.750   1.4392   0.02877   0.02023  -0.0784   0.1939   1.0000
  10.000   1.4494   0.02956   0.02109  -0.0758   0.1760   1.0000
  10.250   1.4597   0.03043   0.02204  -0.0734   0.1587   1.0000
  10.500   1.4688   0.03147   0.02312  -0.0709   0.1417   1.0000
  10.750   1.4752   0.03274   0.02442  -0.0683   0.1273   1.0000
  11.000   1.4775   0.03438   0.02601  -0.0654   0.1122   1.0000
  11.250   1.4777   0.03631   0.02790  -0.0627   0.0992   1.0000
  11.500   1.4773   0.03839   0.03003  -0.0601   0.0885   1.0000
  11.750   1.4752   0.04074   0.03244  -0.0578   0.0779   1.0000
  12.000   1.4714   0.04336   0.03514  -0.0556   0.0681   1.0000
  12.250   1.4660   0.04630   0.03816  -0.0539   0.0590   1.0000
  12.500   1.4611   0.04938   0.04137  -0.0525   0.0507   1.0000
  12.750   1.4538   0.05290   0.04502  -0.0516   0.0457   1.0000
  13.000   1.4447   0.05687   0.04912  -0.0511   0.0425   1.0000
  13.250   1.4330   0.06137   0.05375  -0.0512   0.0407   1.0000
  13.500   1.4207   0.06623   0.05875  -0.0517   0.0395   1.0000
  13.750   1.4083   0.07131   0.06402  -0.0526   0.0385   1.0000
  14.000   1.3952   0.07672   0.06960  -0.0538   0.0378   1.0000
  14.250   1.3820   0.08232   0.07540  -0.0552   0.0371   1.0000
  14.500   1.3690   0.08797   0.08121  -0.0568   0.0366   1.0000
  14.750   1.3571   0.09355   0.08694  -0.0584   0.0361   1.0000
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