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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 50,000
Max Cl/Cd: 38.29 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe134-il-50000-n5.txt
Download as CSV file: xf-goe134-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 134 (MVA H.12) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3716   0.10617   0.09937  -0.0231   1.0000   0.1043
  -8.000  -0.3770   0.10404   0.09734  -0.0247   1.0000   0.1086
  -7.750  -0.3917   0.10282   0.09628  -0.0290   1.0000   0.1105
  -7.500  -0.3839   0.09819   0.09172  -0.0276   1.0000   0.1129
  -7.250  -0.3742   0.09458   0.08814  -0.0255   1.0000   0.1179
  -7.000  -0.3764   0.09201   0.08565  -0.0278   1.0000   0.1237
  -6.750  -0.3826   0.08945   0.08316  -0.0334   1.0000   0.1272
  -6.500  -0.3713   0.08547   0.07926  -0.0284   1.0000   0.1326
  -6.000  -0.3650   0.07942   0.07331  -0.0296   1.0000   0.1487
  -5.750  -0.3621   0.07641   0.07032  -0.0319   1.0000   0.1601
  -5.500  -0.3566   0.07369   0.06756  -0.0334   1.0000   0.1743
  -5.250  -0.3490   0.07059   0.06456  -0.0303   1.0000   0.1828
  -5.000  -0.3421   0.06766   0.06165  -0.0301   1.0000   0.1965
  -4.750  -0.3346   0.06495   0.05895  -0.0298   1.0000   0.2139
  -4.500  -0.3284   0.06235   0.05639  -0.0291   1.0000   0.2392
  -4.000  -0.2512   0.05085   0.04370  -0.0434   1.0000   0.1041
  -3.750  -0.2192   0.04699   0.03900  -0.0455   1.0000   0.0799
  -3.500  -0.1949   0.04383   0.03573  -0.0467   0.9976   0.0767
  -3.250  -0.1514   0.04054   0.03195  -0.0511   0.9897   0.0753
  -3.000  -0.1078   0.03779   0.02868  -0.0550   0.9814   0.0755
  -2.750  -0.0641   0.03524   0.02561  -0.0585   0.9730   0.0732
  -2.500  -0.0206   0.03310   0.02296  -0.0617   0.9642   0.0717
  -2.250   0.0198   0.03144   0.02090  -0.0643   0.9536   0.0730
  -2.000   0.0603   0.03004   0.01915  -0.0667   0.9430   0.0752
  -1.750   0.1046   0.02863   0.01741  -0.0696   0.9345   0.0752
  -1.500   0.1429   0.02750   0.01603  -0.0713   0.9222   0.0754
  -1.250   0.1811   0.02651   0.01485  -0.0728   0.9101   0.0760
  -1.000   0.2196   0.02568   0.01381  -0.0743   0.8979   0.0775
  -0.750   0.2570   0.02501   0.01296  -0.0757   0.8849   0.0810
  -0.500   0.2925   0.02419   0.01210  -0.0769   0.8711   0.0849
  -0.250   0.3269   0.02361   0.01139  -0.0777   0.8560   0.0878
   0.000   0.3604   0.02312   0.01077  -0.0784   0.8403   0.0916
   0.250   0.3934   0.02269   0.01023  -0.0788   0.8242   0.0972
   0.500   0.4259   0.02225   0.00975  -0.0793   0.8079   0.1088
   0.750   0.4541   0.01945   0.00948  -0.0786   0.7925   1.0000
   1.000   0.4850   0.01949   0.00914  -0.0784   0.7758   1.0000
   1.250   0.5149   0.01957   0.00889  -0.0782   0.7592   1.0000
   1.500   0.5440   0.01968   0.00873  -0.0778   0.7426   1.0000
   1.750   0.5723   0.01985   0.00866  -0.0774   0.7260   1.0000
   2.000   0.5991   0.02008   0.00870  -0.0769   0.7084   1.0000
   2.250   0.6255   0.02035   0.00881  -0.0763   0.6908   1.0000
   2.500   0.6520   0.02064   0.00897  -0.0759   0.6734   1.0000
   2.750   0.6783   0.02094   0.00916  -0.0754   0.6562   1.0000
   3.000   0.7045   0.02125   0.00937  -0.0749   0.6393   1.0000
   3.250   0.7305   0.02157   0.00960  -0.0744   0.6227   1.0000
   3.500   0.7565   0.02189   0.00987  -0.0739   0.6064   1.0000
   3.750   0.7823   0.02223   0.01014  -0.0734   0.5905   1.0000
   4.000   0.8081   0.02259   0.01046  -0.0729   0.5750   1.0000
   4.250   0.8338   0.02297   0.01082  -0.0724   0.5597   1.0000
   4.500   0.8593   0.02337   0.01121  -0.0720   0.5449   1.0000
   4.750   0.8847   0.02382   0.01166  -0.0715   0.5305   1.0000
   5.000   0.9099   0.02429   0.01217  -0.0711   0.5164   1.0000
   5.250   0.9351   0.02479   0.01271  -0.0707   0.5030   1.0000
   5.500   0.9601   0.02533   0.01329  -0.0702   0.4902   1.0000
   5.750   0.9853   0.02587   0.01390  -0.0698   0.4781   1.0000
   6.000   1.0108   0.02640   0.01445  -0.0694   0.4669   1.0000
   6.250   1.0348   0.02705   0.01524  -0.0690   0.4548   1.0000
   6.500   1.0587   0.02773   0.01604  -0.0685   0.4433   1.0000
   6.750   1.0830   0.02839   0.01684  -0.0680   0.4326   1.0000
   7.000   1.1078   0.02899   0.01752  -0.0675   0.4223   1.0000
   7.250   1.1297   0.02971   0.01841  -0.0667   0.4097   1.0000
   7.500   1.1513   0.03036   0.01924  -0.0658   0.3963   1.0000
   7.750   1.1724   0.03099   0.02001  -0.0648   0.3826   1.0000
   8.000   1.1931   0.03166   0.02082  -0.0638   0.3693   1.0000
   8.250   1.2138   0.03236   0.02167  -0.0628   0.3567   1.0000
   8.500   1.2343   0.03305   0.02255  -0.0617   0.3442   1.0000
   8.750   1.2539   0.03375   0.02339  -0.0605   0.3311   1.0000
   9.000   1.2719   0.03449   0.02430  -0.0592   0.3172   1.0000
   9.250   1.2878   0.03532   0.02534  -0.0576   0.3027   1.0000
   9.500   1.3024   0.03621   0.02644  -0.0558   0.2880   1.0000
   9.750   1.3157   0.03719   0.02768  -0.0540   0.2734   1.0000
  10.000   1.3270   0.03823   0.02893  -0.0519   0.2587   1.0000
  10.250   1.3351   0.03928   0.03013  -0.0495   0.2428   1.0000
  10.500   1.3374   0.04053   0.03156  -0.0467   0.2255   1.0000
  10.750   1.3351   0.04197   0.03316  -0.0435   0.2077   1.0000
  11.000   1.3292   0.04363   0.03493  -0.0401   0.1916   1.0000
  11.250   1.3241   0.04568   0.03708  -0.0375   0.1765   1.0000
  11.500   1.3183   0.04811   0.03963  -0.0355   0.1623   1.0000
  11.750   1.3097   0.05106   0.04263  -0.0341   0.1478   1.0000
  12.000   1.2990   0.05461   0.04619  -0.0335   0.1338   1.0000
  12.250   1.2878   0.05868   0.05029  -0.0334   0.1215   1.0000
  12.500   1.2762   0.06313   0.05480  -0.0339   0.1110   1.0000
  12.750   1.2629   0.06797   0.05962  -0.0346   0.1027   1.0000
  13.000   1.2509   0.07306   0.06490  -0.0357   0.0931   1.0000
  13.250   1.2376   0.07841   0.07033  -0.0370   0.0851   1.0000
  13.500   1.2240   0.08390   0.07587  -0.0385   0.0784   1.0000
  13.750   1.2117   0.08941   0.08148  -0.0400   0.0715   1.0000
  14.000   1.1996   0.09484   0.08692  -0.0417   0.0665   1.0000
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