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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 200,000
Max Cl/Cd: 73.78 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe277-il-200000-n5.txt
Download as CSV file: xf-goe277-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 277 (DAIMLER VIII) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3434   0.09329   0.08997  -0.0290   1.0000   0.0240
  -7.750  -0.3451   0.09041   0.08715  -0.0297   1.0000   0.0241
  -7.500  -0.3451   0.08729   0.08406  -0.0301   1.0000   0.0240
  -7.250  -0.3440   0.08423   0.08104  -0.0271   1.0000   0.0234
  -7.000  -0.3453   0.08156   0.07841  -0.0258   1.0000   0.0226
  -6.750  -0.3345   0.07750   0.07436  -0.0296   0.9972   0.0220
  -6.500  -0.3080   0.07186   0.06868  -0.0381   0.9911   0.0216
  -6.250  -0.2747   0.06560   0.06232  -0.0486   0.9854   0.0228
  -6.000  -0.2340   0.05763   0.05415  -0.0612   0.9780   0.0239
  -5.750  -0.2005   0.05063   0.04693  -0.0691   0.9721   0.0245
  -5.500  -0.1749   0.04829   0.04456  -0.0718   0.9668   0.0256
  -5.250  -0.1456   0.04632   0.04252  -0.0745   0.9601   0.0281
  -5.000  -0.1094   0.04157   0.03751  -0.0797   0.9524   0.0297
  -4.750  -0.0760   0.03676   0.03238  -0.0835   0.9425   0.0301
  -4.500  -0.0379   0.03236   0.02747  -0.0866   0.9336   0.0326
  -4.000   0.0222   0.02533   0.01957  -0.0896   0.9089   0.0345
  -3.750   0.0497   0.02407   0.01821  -0.0902   0.8938   0.0363
  -3.500   0.0782   0.02235   0.01621  -0.0905   0.8785   0.0372
  -3.250   0.1069   0.02055   0.01404  -0.0905   0.8631   0.0375
  -3.000   0.1350   0.01912   0.01229  -0.0904   0.8457   0.0379
  -2.750   0.1629   0.01805   0.01094  -0.0902   0.8258   0.0389
  -2.500   0.1906   0.01721   0.00984  -0.0899   0.8041   0.0405
  -2.250   0.2182   0.01630   0.00862  -0.0895   0.7816   0.0407
  -2.000   0.2455   0.01552   0.00755  -0.0890   0.7609   0.0409
  -1.750   0.2727   0.01489   0.00668  -0.0886   0.7416   0.0413
  -1.500   0.2998   0.01437   0.00597  -0.0881   0.7228   0.0418
  -1.250   0.3267   0.01394   0.00536  -0.0877   0.7045   0.0425
  -1.000   0.3535   0.01359   0.00487  -0.0873   0.6862   0.0432
  -0.750   0.3804   0.01329   0.00447  -0.0870   0.6675   0.0441
  -0.500   0.4073   0.01315   0.00423  -0.0867   0.6483   0.0456
  -0.250   0.4340   0.01286   0.00386  -0.0864   0.6286   0.0468
   0.000   0.4607   0.01261   0.00353  -0.0861   0.6074   0.0476
   0.250   0.4873   0.01248   0.00328  -0.0858   0.5851   0.0487
   0.500   0.5139   0.01243   0.00311  -0.0855   0.5632   0.0503
   0.750   0.5405   0.01244   0.00298  -0.0852   0.5423   0.0527
   1.000   0.5671   0.01248   0.00290  -0.0849   0.5236   0.0563
   1.250   0.5938   0.01252   0.00286  -0.0846   0.5064   0.0647
   1.750   0.6432   0.01066   0.00301  -0.0834   0.4744   1.0000
   2.000   0.6697   0.01087   0.00308  -0.0832   0.4583   1.0000
   2.250   0.6963   0.01109   0.00316  -0.0829   0.4429   1.0000
   2.500   0.7227   0.01132   0.00328  -0.0827   0.4288   1.0000
   2.750   0.7492   0.01156   0.00341  -0.0824   0.4166   1.0000
   3.000   0.7757   0.01178   0.00355  -0.0822   0.4056   1.0000
   3.250   0.8022   0.01202   0.00373  -0.0820   0.3960   1.0000
   3.500   0.8285   0.01228   0.00391  -0.0817   0.3876   1.0000
   3.750   0.8550   0.01251   0.00412  -0.0815   0.3794   1.0000
   4.000   0.8811   0.01279   0.00435  -0.0813   0.3723   1.0000
   4.250   0.9075   0.01303   0.00458  -0.0811   0.3648   1.0000
   4.500   0.9334   0.01333   0.00483  -0.0808   0.3580   1.0000
   4.750   0.9597   0.01357   0.00510  -0.0806   0.3510   1.0000
   5.000   0.9855   0.01388   0.00539  -0.0803   0.3449   1.0000
   5.250   1.0117   0.01414   0.00569  -0.0801   0.3387   1.0000
   5.500   1.0374   0.01443   0.00599  -0.0798   0.3321   1.0000
   5.750   1.0630   0.01473   0.00633  -0.0795   0.3261   1.0000
   6.000   1.0890   0.01500   0.00667  -0.0793   0.3206   1.0000
   6.250   1.1142   0.01533   0.00702  -0.0789   0.3149   1.0000
   6.500   1.1398   0.01559   0.00738  -0.0786   0.3076   1.0000
   6.750   1.1641   0.01590   0.00772  -0.0782   0.2969   1.0000
   7.000   1.1883   0.01617   0.00804  -0.0777   0.2820   1.0000
   7.250   1.2126   0.01645   0.00837  -0.0772   0.2661   1.0000
   7.500   1.2366   0.01676   0.00874  -0.0767   0.2490   1.0000
   7.750   1.2595   0.01717   0.00916  -0.0761   0.2244   1.0000
   8.000   1.2769   0.01811   0.00977  -0.0749   0.1636   1.0000
   8.250   1.2891   0.01973   0.01098  -0.0731   0.1059   1.0000
   8.500   1.3044   0.02096   0.01207  -0.0716   0.0788   1.0000
   8.750   1.3119   0.02285   0.01359  -0.0692   0.0267   1.0000
   9.000   1.3253   0.02405   0.01486  -0.0673   0.0209   1.0000
   9.250   1.3402   0.02505   0.01600  -0.0656   0.0190   1.0000
   9.500   1.3526   0.02618   0.01728  -0.0636   0.0173   1.0000
   9.750   1.3608   0.02752   0.01875  -0.0611   0.0158   1.0000
  10.000   1.3640   0.02899   0.02038  -0.0580   0.0147   1.0000
  10.250   1.3704   0.03030   0.02186  -0.0555   0.0141   1.0000
  10.500   1.3744   0.03186   0.02357  -0.0530   0.0137   1.0000
  10.750   1.3764   0.03366   0.02553  -0.0508   0.0132   1.0000
  11.000   1.3767   0.03573   0.02779  -0.0488   0.0128   1.0000
  11.250   1.3757   0.03808   0.03029  -0.0471   0.0125   1.0000
  11.500   1.3738   0.04072   0.03307  -0.0459   0.0121   1.0000
  11.750   1.3712   0.04365   0.03614  -0.0452   0.0118   1.0000
  12.000   1.3678   0.04687   0.03949  -0.0449   0.0114   1.0000
  12.250   1.3633   0.05039   0.04313  -0.0449   0.0111   1.0000
  12.500   1.3570   0.05425   0.04710  -0.0451   0.0108   1.0000
  12.750   1.3492   0.05838   0.05134  -0.0454   0.0105   1.0000
  13.000   1.3403   0.06261   0.05566  -0.0456   0.0103   1.0000
  13.250   1.3375   0.06623   0.05940  -0.0459   0.0101   1.0000
  13.500   1.3351   0.06983   0.06312  -0.0463   0.0099   1.0000
  13.750   1.3326   0.07344   0.06686  -0.0466   0.0098   1.0000
  14.000   1.3302   0.07710   0.07065  -0.0470   0.0096   1.0000
  14.250   1.3279   0.08080   0.07449  -0.0474   0.0095   1.0000
  14.500   1.3254   0.08456   0.07839  -0.0479   0.0093   1.0000
  14.750   1.3228   0.08840   0.08239  -0.0485   0.0092   1.0000
  15.000   1.3200   0.09237   0.08650  -0.0493   0.0091   1.0000
  15.250   1.3164   0.09654   0.09082  -0.0502   0.0089   1.0000
  15.500   1.3122   0.10089   0.09533  -0.0514   0.0088   1.0000
  15.750   1.3071   0.10554   0.10013  -0.0529   0.0087   1.0000
  16.000   1.3012   0.11044   0.10520  -0.0547   0.0086   1.0000
  16.250   1.2947   0.11561   0.11053  -0.0568   0.0085   1.0000
  16.500   1.2875   0.12104   0.11612  -0.0593   0.0085   1.0000
  16.750   1.2797   0.12672   0.12196  -0.0621   0.0083   1.0000
  17.000   1.2716   0.13262   0.12802  -0.0652   0.0083   1.0000
  17.250   1.2634   0.13873   0.13428  -0.0686   0.0082   1.0000
  17.500   1.2542   0.14526   0.14097  -0.0723   0.0081   1.0000
  17.750   1.2454   0.15191   0.14777  -0.0763   0.0080   1.0000
  18.000   1.2350   0.15922   0.15525  -0.0809   0.0080   1.0000
  18.250   1.2248   0.16677   0.16294  -0.0857   0.0080   1.0000
  18.500   1.2101   0.17618   0.17254  -0.0919   0.0081   1.0000
  18.750   1.1917   0.18765   0.18420  -0.0994   0.0083   1.0000
  19.000   1.1650   0.20382   0.20056  -0.1096   0.0087   1.0000
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