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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 200,000
Max Cl/Cd: 82.33 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe210-il-200000.txt
Download as CSV file: xf-goe210-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3543   0.09010   0.08671  -0.0217   1.0000   0.0283
  -7.250  -0.3534   0.08753   0.08421  -0.0223   1.0000   0.0288
  -7.000  -0.3501   0.08475   0.08148  -0.0237   1.0000   0.0295
  -6.750  -0.3462   0.08197   0.07875  -0.0254   1.0000   0.0302
  -6.500  -0.3410   0.07924   0.07606  -0.0278   1.0000   0.0310
  -6.250  -0.3320   0.07668   0.07352  -0.0323   1.0000   0.0319
  -6.000  -0.3207   0.07417   0.07099  -0.0364   1.0000   0.0323
  -5.750  -0.3139   0.07174   0.06854  -0.0379   1.0000   0.0325
  -5.500  -0.3092   0.06947   0.06624  -0.0381   0.9997   0.0326
  -5.250  -0.2821   0.06183   0.05856  -0.0444   0.9957   0.0334
  -5.000  -0.2582   0.05768   0.05441  -0.0469   0.9915   0.0347
  -4.750  -0.2229   0.05365   0.05031  -0.0524   0.9866   0.0370
  -4.500  -0.1550   0.05011   0.04621  -0.0642   0.9817   0.0438
  -4.250  -0.1293   0.04366   0.03977  -0.0683   0.9759   0.0456
  -4.000  -0.0949   0.04051   0.03659  -0.0721   0.9720   0.0487
  -3.750  -0.0435   0.03696   0.03241  -0.0781   0.9667   0.0572
  -3.500  -0.0142   0.03365   0.02920  -0.0808   0.9611   0.0608
  -3.250   0.0297   0.03072   0.02593  -0.0851   0.9577   0.0724
  -3.000   0.0701   0.02851   0.02338  -0.0883   0.9533   0.0855
  -2.750   0.1065   0.02673   0.02130  -0.0905   0.9468   0.0989
  -2.500   0.1443   0.02438   0.01878  -0.0933   0.9430   0.1134
  -2.250   0.1748   0.02237   0.01678  -0.0946   0.9355   0.1306
  -2.000   0.2211   0.01868   0.01206  -0.0945   0.9307   0.0674
  -1.750   0.2557   0.01689   0.01000  -0.0954   0.9248   0.0653
  -1.500   0.2872   0.01565   0.00853  -0.0956   0.9168   0.0648
  -1.250   0.3182   0.01459   0.00730  -0.0956   0.9085   0.0645
  -1.000   0.3488   0.01378   0.00638  -0.0954   0.8996   0.0664
  -0.750   0.3761   0.01323   0.00574  -0.0945   0.8865   0.0691
  -0.500   0.4023   0.01247   0.00494  -0.0935   0.8723   0.0705
  -0.250   0.4284   0.01188   0.00437  -0.0926   0.8585   0.0742
   0.000   0.4549   0.01158   0.00404  -0.0919   0.8461   0.0799
   0.250   0.4815   0.01131   0.00375  -0.0912   0.8337   0.0919
   0.500   0.5057   0.00885   0.00352  -0.0902   0.8213   1.0000
   0.750   0.5320   0.00894   0.00337  -0.0893   0.8075   1.0000
   1.000   0.5584   0.00904   0.00332  -0.0887   0.7951   1.0000
   1.250   0.5852   0.00916   0.00330  -0.0881   0.7843   1.0000
   1.500   0.6117   0.00928   0.00334  -0.0876   0.7723   1.0000
   1.750   0.6381   0.00939   0.00338  -0.0871   0.7600   1.0000
   2.000   0.6645   0.00950   0.00342  -0.0865   0.7474   1.0000
   2.250   0.6908   0.00960   0.00347  -0.0860   0.7338   1.0000
   2.500   0.7168   0.00969   0.00351  -0.0853   0.7180   1.0000
   2.750   0.7425   0.00976   0.00351  -0.0845   0.6993   1.0000
   3.000   0.7679   0.00983   0.00353  -0.0837   0.6764   1.0000
   3.250   0.7931   0.00992   0.00354  -0.0828   0.6496   1.0000
   3.500   0.8179   0.01004   0.00358  -0.0819   0.6161   1.0000
   3.750   0.8422   0.01023   0.00364  -0.0810   0.5736   1.0000
   4.000   0.8651   0.01058   0.00373  -0.0799   0.5152   1.0000
   4.250   0.8859   0.01122   0.00396  -0.0785   0.4397   1.0000
   4.500   0.9063   0.01200   0.00438  -0.0773   0.3721   1.0000
   4.750   0.9279   0.01273   0.00483  -0.0764   0.3249   1.0000
   5.000   0.9507   0.01336   0.00529  -0.0756   0.2936   1.0000
   5.250   0.9740   0.01392   0.00573  -0.0750   0.2718   1.0000
   5.500   0.9976   0.01444   0.00620  -0.0744   0.2556   1.0000
   5.750   1.0218   0.01490   0.00665  -0.0738   0.2432   1.0000
   6.000   1.0460   0.01534   0.00711  -0.0733   0.2324   1.0000
   6.250   1.0700   0.01578   0.00757  -0.0727   0.2208   1.0000
   6.500   1.0937   0.01623   0.00805  -0.0722   0.2084   1.0000
   6.750   1.1172   0.01668   0.00851  -0.0716   0.1946   1.0000
   7.000   1.1405   0.01712   0.00899  -0.0710   0.1799   1.0000
   7.250   1.1636   0.01757   0.00945  -0.0704   0.1621   1.0000
   7.500   1.1865   0.01805   0.00995  -0.0698   0.1448   1.0000
   7.750   1.2098   0.01849   0.01045  -0.0692   0.1236   1.0000
   8.000   1.2318   0.01908   0.01096  -0.0684   0.1006   1.0000
   8.250   1.2521   0.01987   0.01166  -0.0675   0.0843   1.0000
   8.500   1.2707   0.02087   0.01262  -0.0663   0.0704   1.0000
   8.750   1.2867   0.02217   0.01391  -0.0648   0.0552   1.0000
   9.000   1.3054   0.02319   0.01507  -0.0635   0.0392   1.0000
   9.250   1.3221   0.02435   0.01624  -0.0619   0.0308   1.0000
   9.500   1.3374   0.02555   0.01748  -0.0602   0.0270   1.0000
   9.750   1.3481   0.02710   0.01915  -0.0579   0.0251   1.0000
  10.000   1.3591   0.02853   0.02073  -0.0557   0.0237   1.0000
  10.250   1.3687   0.02997   0.02229  -0.0534   0.0221   1.0000
  10.500   1.3738   0.03157   0.02400  -0.0506   0.0209   1.0000
  10.750   1.3762   0.03354   0.02611  -0.0476   0.0203   1.0000
  11.000   1.3776   0.03582   0.02852  -0.0448   0.0198   1.0000
  11.250   1.3792   0.03848   0.03135  -0.0421   0.0194   1.0000
  11.500   1.3816   0.04146   0.03451  -0.0398   0.0191   1.0000
  11.750   1.3850   0.04410   0.03738  -0.0377   0.0190   1.0000
  12.000   1.3861   0.04702   0.04055  -0.0358   0.0189   1.0000
  12.250   1.3844   0.05027   0.04406  -0.0340   0.0189   1.0000
  12.500   1.3795   0.05385   0.04791  -0.0325   0.0189   1.0000
  12.750   1.3712   0.05782   0.05214  -0.0313   0.0189   1.0000
  13.000   1.3600   0.06218   0.05678  -0.0307   0.0190   1.0000
  13.250   1.3463   0.06692   0.06177  -0.0307   0.0190   1.0000
  13.500   1.3308   0.07207   0.06716  -0.0314   0.0190   1.0000
  13.750   1.3131   0.07781   0.07313  -0.0328   0.0191   1.0000
  14.000   1.2949   0.08394   0.07949  -0.0349   0.0192   1.0000
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