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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 50,000
Max Cl/Cd: 38.6 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe277-il-50000-n5.txt
Download as CSV file: xf-goe277-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3476   0.11121   0.10433  -0.0228   1.0000   0.0864
  -8.500  -0.3541   0.11013   0.10338  -0.0255   1.0000   0.0881
  -8.250  -0.3624   0.10905   0.10244  -0.0281   1.0000   0.0887
  -8.000  -0.3398   0.10212   0.09548  -0.0246   1.0000   0.0931
  -7.750  -0.3369   0.09943   0.09286  -0.0244   1.0000   0.0978
  -7.500  -0.3423   0.09774   0.09130  -0.0259   1.0000   0.1018
  -7.250  -0.3492   0.09676   0.09043  -0.0317   1.0000   0.1038
  -7.000  -0.3411   0.09190   0.08565  -0.0282   1.0000   0.1065
  -6.750  -0.3352   0.08877   0.08257  -0.0267   1.0000   0.1105
  -6.500  -0.3337   0.08631   0.08019  -0.0282   1.0000   0.1157
  -6.250  -0.3328   0.08455   0.07844  -0.0356   1.0000   0.1195
  -6.000  -0.3275   0.08039   0.07438  -0.0305   1.0000   0.1225
  -5.750  -0.3221   0.07772   0.07175  -0.0299   1.0000   0.1292
  -5.500  -0.3166   0.07479   0.06885  -0.0324   1.0000   0.1369
  -5.250  -0.3063   0.07266   0.06663  -0.0365   1.0000   0.1497
  -5.000  -0.3032   0.06929   0.06338  -0.0316   1.0000   0.1552
  -4.750  -0.2925   0.06649   0.06054  -0.0339   1.0000   0.1670
  -4.500  -0.2801   0.06393   0.05792  -0.0357   1.0000   0.1808
  -4.250  -0.2719   0.06107   0.05512  -0.0337   1.0000   0.1868
  -4.000  -0.2164   0.05393   0.04711  -0.0460   1.0000   0.1028
  -3.750  -0.1699   0.04864   0.04136  -0.0523   0.9933   0.0871
  -3.500  -0.1278   0.04453   0.03697  -0.0574   0.9860   0.0817
  -3.250  -0.0817   0.04071   0.03256  -0.0626   0.9778   0.0783
  -3.000  -0.0396   0.03809   0.02954  -0.0667   0.9688   0.0812
  -2.750   0.0046   0.03537   0.02629  -0.0706   0.9601   0.0798
  -2.500   0.0499   0.03298   0.02334  -0.0743   0.9514   0.0784
  -2.250   0.0918   0.03105   0.02092  -0.0771   0.9399   0.0779
  -2.000   0.1351   0.02939   0.01888  -0.0799   0.9274   0.0789
  -1.750   0.1786   0.02806   0.01723  -0.0826   0.9139   0.0838
  -1.500   0.2206   0.02677   0.01558  -0.0847   0.8998   0.0858
  -1.250   0.2585   0.02563   0.01419  -0.0858   0.8848   0.0868
  -1.000   0.2947   0.02471   0.01301  -0.0865   0.8695   0.0882
  -0.750   0.3292   0.02384   0.01201  -0.0870   0.8538   0.0903
  -0.500   0.3624   0.02310   0.01119  -0.0874   0.8375   0.0937
  -0.250   0.3951   0.02248   0.01044  -0.0876   0.8207   0.0989
   0.000   0.4256   0.02196   0.00988  -0.0876   0.8021   0.1104
   0.250   0.4563   0.02145   0.00936  -0.0876   0.7832   0.1288
   0.500   0.4876   0.02059   0.00888  -0.0878   0.7648   0.2059
   1.000   0.5428   0.01873   0.00817  -0.0857   0.7260   1.0000
   1.250   0.5705   0.01889   0.00802  -0.0851   0.7056   1.0000
   1.500   0.5980   0.01907   0.00793  -0.0845   0.6857   1.0000
   1.750   0.6235   0.01934   0.00801  -0.0837   0.6638   1.0000
   2.000   0.6496   0.01960   0.00808  -0.0830   0.6437   1.0000
   2.250   0.6758   0.01990   0.00819  -0.0824   0.6240   1.0000
   2.500   0.7015   0.02023   0.00838  -0.0818   0.6045   1.0000
   2.750   0.7275   0.02057   0.00859  -0.0813   0.5867   1.0000
   3.000   0.7536   0.02093   0.00882  -0.0808   0.5703   1.0000
   3.250   0.7797   0.02133   0.00911  -0.0803   0.5550   1.0000
   3.500   0.8058   0.02177   0.00948  -0.0799   0.5406   1.0000
   3.750   0.8319   0.02223   0.00989  -0.0796   0.5273   1.0000
   4.000   0.8581   0.02273   0.01035  -0.0793   0.5153   1.0000
   4.250   0.8845   0.02324   0.01084  -0.0790   0.5046   1.0000
   4.500   0.9105   0.02377   0.01138  -0.0788   0.4940   1.0000
   4.750   0.9360   0.02437   0.01204  -0.0785   0.4840   1.0000
   5.000   0.9623   0.02494   0.01264  -0.0782   0.4758   1.0000
   5.250   0.9873   0.02560   0.01342  -0.0780   0.4668   1.0000
   5.500   1.0129   0.02624   0.01414  -0.0777   0.4591   1.0000
   5.750   1.0377   0.02693   0.01496  -0.0774   0.4512   1.0000
   6.000   1.0628   0.02764   0.01582  -0.0771   0.4442   1.0000
   6.250   1.0870   0.02841   0.01676  -0.0767   0.4367   1.0000
   6.500   1.1117   0.02915   0.01764  -0.0763   0.4300   1.0000
   6.750   1.1347   0.03001   0.01873  -0.0758   0.4225   1.0000
   7.000   1.1589   0.03075   0.01967  -0.0753   0.4154   1.0000
   7.250   1.1811   0.03148   0.02060  -0.0745   0.4058   1.0000
   7.500   1.2016   0.03212   0.02143  -0.0734   0.3938   1.0000
   7.750   1.2220   0.03261   0.02209  -0.0722   0.3806   1.0000
   8.000   1.2422   0.03313   0.02281  -0.0710   0.3678   1.0000
   8.250   1.2642   0.03366   0.02350  -0.0700   0.3572   1.0000
   8.500   1.2831   0.03453   0.02468  -0.0688   0.3468   1.0000
   8.750   1.3008   0.03534   0.02579  -0.0674   0.3349   1.0000
   9.000   1.3159   0.03564   0.02623  -0.0654   0.3170   1.0000
   9.250   1.3264   0.03599   0.02678  -0.0629   0.2964   1.0000
   9.500   1.3335   0.03674   0.02782  -0.0603   0.2756   1.0000
   9.750   1.3389   0.03752   0.02881  -0.0576   0.2530   1.0000
  10.000   1.3400   0.03868   0.03020  -0.0548   0.2240   1.0000
  10.250   1.3340   0.04020   0.03164  -0.0514   0.1858   1.0000
  10.500   1.3232   0.04258   0.03373  -0.0484   0.1499   1.0000
  10.750   1.3106   0.04581   0.03678  -0.0462   0.1258   1.0000
  11.000   1.2965   0.04972   0.04063  -0.0450   0.1086   1.0000
  11.250   1.2816   0.05421   0.04514  -0.0447   0.0957   1.0000
  11.500   1.2665   0.05918   0.05017  -0.0451   0.0856   1.0000
  11.750   1.2504   0.06459   0.05561  -0.0462   0.0786   1.0000
  12.000   1.2372   0.06993   0.06111  -0.0474   0.0704   1.0000
  12.250   1.2230   0.07550   0.06670  -0.0488   0.0654   1.0000
  12.500   1.2122   0.08067   0.07201  -0.0500   0.0595   1.0000
  12.750   1.2006   0.08596   0.07734  -0.0514   0.0558   1.0000
  13.000   1.1919   0.09083   0.08225  -0.0525   0.0523   1.0000
  13.250   1.1852   0.09540   0.08692  -0.0534   0.0493   1.0000
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