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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 100,000
Max Cl/Cd: 62.04 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe210-il-100000.txt
Download as CSV file: xf-goe210-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3636   0.09956   0.09470  -0.0206   1.0000   0.0536
  -7.750  -0.3639   0.09772   0.09294  -0.0227   1.0000   0.0549
  -7.500  -0.3638   0.09630   0.09162  -0.0275   1.0000   0.0557
  -7.250  -0.3578   0.09449   0.08985  -0.0344   1.0000   0.0562
  -7.000  -0.3501   0.09151   0.08691  -0.0388   1.0000   0.0565
  -6.750  -0.3485   0.08518   0.08067  -0.0285   1.0000   0.0586
  -6.500  -0.3429   0.08222   0.07776  -0.0272   1.0000   0.0612
  -6.250  -0.3372   0.07950   0.07509  -0.0283   1.0000   0.0643
  -6.000  -0.3276   0.07715   0.07275  -0.0332   1.0000   0.0681
  -5.750  -0.3063   0.07652   0.07185  -0.0443   1.0000   0.0697
  -5.500  -0.3124   0.07069   0.06631  -0.0377   1.0000   0.0711
  -5.250  -0.3114   0.06791   0.06359  -0.0345   1.0000   0.0730
  -5.000  -0.3071   0.06551   0.06123  -0.0336   1.0000   0.0758
  -4.750  -0.2968   0.06309   0.05875  -0.0351   1.0000   0.0803
  -4.500  -0.2736   0.06017   0.05557  -0.0413   1.0000   0.0846
  -4.250  -0.2710   0.05708   0.05260  -0.0386   1.0000   0.0868
  -4.000  -0.2590   0.05462   0.05012  -0.0385   1.0000   0.0916
  -3.750  -0.2321   0.05155   0.04678  -0.0429   1.0000   0.0994
  -3.500  -0.2200   0.04896   0.04423  -0.0422   1.0000   0.1048
  -3.250  -0.1970   0.04621   0.04131  -0.0444   1.0000   0.1161
  -3.000  -0.1625   0.04320   0.03814  -0.0482   0.9970   0.1328
  -2.750  -0.1178   0.04009   0.03474  -0.0540   0.9926   0.1573
  -2.500  -0.0793   0.03730   0.03181  -0.0580   0.9876   0.1866
  -2.250  -0.0427   0.03470   0.02922  -0.0613   0.9836   0.2326
  -2.000  -0.0147   0.03254   0.02712  -0.0626   0.9779   0.3031
  -1.750   0.0190   0.03026   0.02493  -0.0640   0.9731   0.3650
  -1.500   0.1192   0.02667   0.01905  -0.0741   0.9707   0.1214
  -1.250   0.1617   0.02479   0.01662  -0.0760   0.9653   0.1043
  -1.000   0.2053   0.02380   0.01504  -0.0781   0.9594   0.0972
  -0.750   0.2507   0.02235   0.01354  -0.0816   0.9554   0.1025
  -0.500   0.2855   0.02157   0.01265  -0.0829   0.9470   0.1036
  -0.250   0.3322   0.02071   0.01175  -0.0862   0.9417   0.1075
   0.000   0.3673   0.02004   0.01113  -0.0875   0.9317   0.1150
   0.250   0.4099   0.01931   0.01049  -0.0900   0.9223   0.1343
   0.500   0.4587   0.01635   0.00952  -0.0928   0.9152   1.0000
   0.750   0.4991   0.01614   0.00903  -0.0943   0.9024   1.0000
   1.000   0.5378   0.01583   0.00855  -0.0954   0.8888   1.0000
   1.250   0.5741   0.01544   0.00806  -0.0957   0.8744   1.0000
   1.500   0.6066   0.01516   0.00769  -0.0954   0.8603   1.0000
   1.750   0.6363   0.01503   0.00750  -0.0949   0.8470   1.0000
   2.000   0.6648   0.01496   0.00739  -0.0942   0.8338   1.0000
   2.250   0.6925   0.01490   0.00729  -0.0933   0.8197   1.0000
   2.500   0.7195   0.01486   0.00724  -0.0922   0.8045   1.0000
   2.750   0.7458   0.01484   0.00719  -0.0910   0.7885   1.0000
   3.000   0.7719   0.01483   0.00716  -0.0897   0.7719   1.0000
   3.250   0.7968   0.01487   0.00719  -0.0883   0.7533   1.0000
   3.500   0.8212   0.01489   0.00725  -0.0869   0.7321   1.0000
   3.750   0.8457   0.01486   0.00721  -0.0853   0.7090   1.0000
   4.000   0.8695   0.01481   0.00716  -0.0836   0.6808   1.0000
   4.250   0.8922   0.01473   0.00703  -0.0817   0.6425   1.0000
   4.500   0.9136   0.01473   0.00693  -0.0795   0.5872   1.0000
   4.750   0.9331   0.01504   0.00686  -0.0771   0.5097   1.0000
   5.000   0.9513   0.01586   0.00715  -0.0750   0.4342   1.0000
   5.250   0.9711   0.01682   0.00772  -0.0736   0.3862   1.0000
   5.500   0.9929   0.01772   0.00841  -0.0725   0.3561   1.0000
   5.750   1.0158   0.01851   0.00909  -0.0717   0.3327   1.0000
   6.000   1.0390   0.01928   0.00978  -0.0710   0.3146   1.0000
   6.250   1.0628   0.02004   0.01050  -0.0703   0.2998   1.0000
   6.500   1.0861   0.02076   0.01122  -0.0697   0.2848   1.0000
   6.750   1.1096   0.02149   0.01203  -0.0690   0.2713   1.0000
   7.000   1.1328   0.02223   0.01286  -0.0683   0.2577   1.0000
   7.250   1.1553   0.02301   0.01370  -0.0675   0.2430   1.0000
   7.500   1.1758   0.02379   0.01454  -0.0665   0.2244   1.0000
   7.750   1.1943   0.02451   0.01535  -0.0652   0.2023   1.0000
   8.000   1.2118   0.02531   0.01618  -0.0639   0.1804   1.0000
   8.250   1.2296   0.02611   0.01705  -0.0626   0.1613   1.0000
   8.500   1.2482   0.02701   0.01806  -0.0613   0.1464   1.0000
   8.750   1.2663   0.02776   0.01898  -0.0600   0.1324   1.0000
   9.000   1.2827   0.02818   0.01958  -0.0586   0.1137   1.0000
   9.250   1.2962   0.02916   0.02055  -0.0569   0.0882   1.0000
   9.500   1.2986   0.03193   0.02309  -0.0538   0.0682   1.0000
   9.750   1.3054   0.03466   0.02586  -0.0511   0.0577   1.0000
  10.000   1.3160   0.03730   0.02866  -0.0489   0.0512   1.0000
  10.250   1.3262   0.03942   0.03087  -0.0469   0.0461   1.0000
  10.500   1.3408   0.04289   0.03438  -0.0456   0.0431   1.0000
  10.750   1.3521   0.04552   0.03740  -0.0436   0.0414   1.0000
  11.000   1.3603   0.04858   0.04082  -0.0415   0.0401   1.0000
  11.250   1.3627   0.05177   0.04440  -0.0389   0.0392   1.0000
  11.500   1.3598   0.05505   0.04802  -0.0362   0.0386   1.0000
  11.750   1.3525   0.05837   0.05165  -0.0336   0.0381   1.0000
  12.000   1.3420   0.06185   0.05543  -0.0314   0.0376   1.0000
  12.250   1.3292   0.06560   0.05945  -0.0298   0.0372   1.0000
  12.500   1.3131   0.06988   0.06401  -0.0291   0.0370   1.0000
  12.750   1.2916   0.07506   0.06948  -0.0294   0.0372   1.0000
  13.000   1.2640   0.08157   0.07630  -0.0312   0.0379   1.0000
  13.250   1.2345   0.08912   0.08413  -0.0347   0.0387   1.0000
  13.500   1.2046   0.09773   0.09296  -0.0396   0.0397   1.0000
  13.750   1.1751   0.10741   0.10278  -0.0459   0.0406   1.0000
  14.000   1.1460   0.11829   0.11378  -0.0532   0.0415   1.0000
  14.250   1.1189   0.12992   0.12546  -0.0608   0.0425   1.0000
  14.500   1.0981   0.14068   0.13621  -0.0669   0.0433   1.0000
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