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GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il)
Reynolds number: 50,000
Max Cl/Cd: 15.19 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe255-il-50000-n5.txt
Download as CSV file: xf-goe255-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 255 (MVA CA.6) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3668   0.11081   0.10449  -0.0596   1.0000   0.0592
 -11.750  -0.3973   0.10472   0.09854  -0.0598   1.0000   0.0592
 -11.500  -0.4401   0.09668   0.09062  -0.0613   0.9997   0.0585
 -11.250  -0.4945   0.08060   0.07432  -0.0731   0.9922   0.0569
 -11.000  -0.5206   0.07078   0.06418  -0.0823   0.9827   0.0568
 -10.750  -0.5307   0.06415   0.05725  -0.0893   0.9722   0.0576
 -10.500  -0.5372   0.05921   0.05201  -0.0941   0.9601   0.0590
 -10.250  -0.5401   0.05527   0.04771  -0.0966   0.9474   0.0611
 -10.000  -0.5341   0.05221   0.04440  -0.0979   0.9356   0.0640
  -9.750  -0.5198   0.05009   0.04223  -0.0991   0.9258   0.0679
  -9.500  -0.5051   0.04732   0.03909  -0.1004   0.9172   0.0732
  -9.250  -0.4953   0.04556   0.03734  -0.0999   0.9066   0.0783
  -9.000  -0.4772   0.04330   0.03481  -0.1010   0.8994   0.0875
  -8.750  -0.4650   0.04178   0.03332  -0.1005   0.8899   0.0965
  -8.500  -0.4493   0.04025   0.03175  -0.1006   0.8816   0.1089
  -8.250  -0.4292   0.03881   0.03019  -0.1012   0.8742   0.1260
  -8.000  -0.4123   0.03783   0.02915  -0.1010   0.8657   0.1440
  -7.750  -0.3883   0.03694   0.02821  -0.1017   0.8591   0.1650
  -7.500  -0.3687   0.03613   0.02727  -0.1014   0.8512   0.1846
  -7.250  -0.3437   0.03516   0.02613  -0.1018   0.8447   0.2054
  -7.000  -0.3177   0.03447   0.02543  -0.1020   0.8386   0.2240
  -6.750  -0.2956   0.03402   0.02497  -0.1014   0.8309   0.2417
  -6.500  -0.2632   0.03353   0.02443  -0.1023   0.8265   0.2612
  -6.250  -0.2446   0.03350   0.02436  -0.1010   0.8176   0.2770
  -6.000  -0.2140   0.03329   0.02403  -0.1014   0.8122   0.2956
  -5.750  -0.1892   0.03326   0.02386  -0.1011   0.8053   0.3132
  -5.500  -0.1644   0.03323   0.02364  -0.1008   0.7982   0.3320
  -5.250  -0.1315   0.03321   0.02349  -0.1014   0.7939   0.3513
  -5.000  -0.1147   0.03347   0.02364  -0.0998   0.7850   0.3673
  -4.750  -0.0862   0.03336   0.02336  -0.1000   0.7798   0.3847
  -4.500  -0.0529   0.03306   0.02287  -0.1009   0.7763   0.4021
  -4.250  -0.0399   0.03333   0.02302  -0.0990   0.7667   0.4152
  -4.000  -0.0097   0.03310   0.02261  -0.0995   0.7621   0.4310
  -3.750   0.0143   0.03312   0.02250  -0.0990   0.7562   0.4449
  -3.500   0.0336   0.03332   0.02265  -0.0979   0.7489   0.4563
  -3.250   0.0641   0.03315   0.02235  -0.0983   0.7450   0.4703
  -3.000   0.0847   0.03338   0.02243  -0.0977   0.7389   0.4828
  -2.750   0.1027   0.03374   0.02275  -0.0965   0.7324   0.4936
  -2.500   0.1311   0.03373   0.02264  -0.0967   0.7287   0.5059
  -2.250   0.1636   0.03359   0.02235  -0.0975   0.7261   0.5189
  -2.000   0.1672   0.03460   0.02337  -0.0946   0.7168   0.5275
  -1.750   0.1941   0.03470   0.02339  -0.0947   0.7128   0.5393
  -1.500   0.2256   0.03466   0.02323  -0.0954   0.7100   0.5528
  -1.250   0.2289   0.03586   0.02445  -0.0927   0.7020   0.5624
  -1.000   0.2501   0.03632   0.02488  -0.0921   0.6978   0.5748
  -0.750   0.2776   0.03652   0.02502  -0.0924   0.6950   0.5884
  -0.250   0.3001   0.03843   0.02694  -0.0893   0.6834   0.6085
   0.000   0.3256   0.03877   0.02723  -0.0894   0.6799   0.6203
   0.250   0.3560   0.03889   0.02732  -0.0900   0.6776   0.6325
   0.750   0.3711   0.04136   0.02987  -0.0865   0.6648   0.6553
   1.000   0.4045   0.04106   0.02959  -0.0870   0.6617   0.6727
   1.500   0.4312   0.04266   0.03137  -0.0841   0.6479   0.7121
   1.750   0.4667   0.04182   0.03065  -0.0841   0.6450   0.7493
   2.250   0.5035   0.04240   0.03161  -0.0817   0.6300   1.0000
   2.500   0.5081   0.04405   0.03315  -0.0803   0.6195   1.0000
   2.750   0.5421   0.04394   0.03286  -0.0812   0.6153   1.0000
   3.000   0.5784   0.04365   0.03242  -0.0822   0.6124   1.0000
   3.250   0.5731   0.04612   0.03486  -0.0800   0.6013   1.0000
   3.500   0.6087   0.04580   0.03443  -0.0807   0.5982   1.0000
   3.750   0.6069   0.04803   0.03664  -0.0787   0.5872   1.0000
   4.000   0.6399   0.04781   0.03635  -0.0791   0.5834   1.0000
   4.500   0.6728   0.04968   0.03816  -0.0776   0.5683   1.0000
   4.750   0.7083   0.04914   0.03757  -0.0779   0.5653   1.0000
   5.000   0.7074   0.05133   0.03978  -0.0761   0.5527   1.0000
   5.250   0.7371   0.05116   0.03958  -0.0759   0.5481   1.0000
   5.500   0.7427   0.05287   0.04131  -0.0745   0.5365   1.0000
   5.750   0.7782   0.05215   0.04057  -0.0746   0.5336   1.0000
   6.000   0.7764   0.05458   0.04304  -0.0729   0.5199   1.0000
   6.250   0.8111   0.05385   0.04231  -0.0729   0.5170   1.0000
   6.500   0.8089   0.05639   0.04489  -0.0712   0.5029   1.0000
   6.750   0.8436   0.05555   0.04405  -0.0711   0.5001   1.0000
   7.000   0.8391   0.05841   0.04695  -0.0696   0.4857   1.0000
   7.250   0.8732   0.05761   0.04617  -0.0693   0.4831   1.0000
   7.750   0.8568   0.06476   0.05341  -0.0668   0.4553   1.0000
   8.000   0.8860   0.06438   0.05306  -0.0664   0.4521   1.0000
   8.250   0.8754   0.06848   0.05721  -0.0655   0.4389   1.0000
   8.500   0.9038   0.06820   0.05698  -0.0651   0.4362   1.0000
   8.750   0.8888   0.07309   0.06192  -0.0644   0.4236   1.0000
   9.000   0.9173   0.07271   0.06160  -0.0640   0.4210   1.0000
   9.250   0.9027   0.07757   0.06651  -0.0634   0.4088   1.0000
   9.500   0.9316   0.07694   0.06594  -0.0628   0.4056   1.0000
   9.750   0.9217   0.08112   0.07019  -0.0624   0.3940   1.0000
  10.250   0.9421   0.08442   0.07361  -0.0613   0.3795   1.0000
  10.500   0.9742   0.08310   0.07237  -0.0605   0.3769   1.0000
  11.000   0.9859   0.08782   0.07725  -0.0597   0.3626   1.0000
  11.500   0.9936   0.09327   0.08287  -0.0592   0.3482   1.0000
  12.000   0.9998   0.09903   0.08880  -0.0589   0.3333   1.0000
  12.250   1.0307   0.09762   0.08751  -0.0579   0.3310   1.0000
  12.750   1.0291   0.10471   0.09479  -0.0580   0.3153   1.0000
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