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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 500,000
Max Cl/Cd: 93.42 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe114-il-500000.txt
Download as CSV file: xf-goe114-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 114 (MVA MK.1) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3647   0.09703   0.09480  -0.0426   1.0000   0.0090
  -9.250  -0.3636   0.09340   0.09121  -0.0436   1.0000   0.0090
  -7.750  -0.3767   0.06681   0.06479  -0.0569   0.9937   0.0090
  -7.500  -0.3527   0.05621   0.05399  -0.0780   0.9838   0.0090
  -7.250  -0.3337   0.04964   0.04711  -0.0886   0.9757   0.0090
  -7.000  -0.3177   0.04045   0.03745  -0.0981   0.9699   0.0094
  -6.750  -0.3030   0.03329   0.02989  -0.1022   0.9615   0.0101
  -6.500  -0.2786   0.02970   0.02619  -0.1051   0.9565   0.0116
  -6.250  -0.2559   0.02704   0.02325  -0.1061   0.9478   0.0126
  -6.000  -0.2300   0.02460   0.02048  -0.1070   0.9411   0.0136
  -5.750  -0.2074   0.02270   0.01828  -0.1066   0.9314   0.0148
  -5.500  -0.1832   0.02121   0.01650  -0.1060   0.9223   0.0164
  -5.250  -0.1540   0.02183   0.01689  -0.1057   0.9147   0.0188
  -5.000  -0.1305   0.02079   0.01553  -0.1048   0.9052   0.0190
  -4.750  -0.1121   0.01604   0.01045  -0.1040   0.8967   0.0227
  -4.500  -0.0870   0.01476   0.00907  -0.1036   0.8895   0.0262
  -4.250  -0.0615   0.01388   0.00805  -0.1029   0.8813   0.0294
  -4.000  -0.0340   0.01250   0.00653  -0.1014   0.8747   0.0153
  -3.750  -0.0099   0.01144   0.00537  -0.1003   0.8667   0.0139
  -3.500   0.0152   0.01067   0.00445  -0.0996   0.8600   0.0152
  -3.250   0.0410   0.01023   0.00392  -0.0992   0.8525   0.0178
  -3.000   0.0673   0.00975   0.00326  -0.0988   0.8459   0.0185
  -2.750   0.0938   0.00938   0.00273  -0.0984   0.8389   0.0189
  -2.500   0.1209   0.00909   0.00221  -0.0981   0.8325   0.0232
  -2.250   0.1452   0.00823   0.00175  -0.0977   0.8256   0.1706
  -2.000   0.1708   0.00793   0.00189  -0.0976   0.8192   0.3128
  -1.750   0.1984   0.00805   0.00195  -0.0975   0.8124   0.3330
  -1.500   0.2259   0.00815   0.00198  -0.0975   0.8061   0.3470
  -1.250   0.2531   0.00822   0.00204  -0.0974   0.7993   0.3585
  -1.000   0.2803   0.00818   0.00197  -0.0973   0.7930   0.3622
  -0.750   0.3074   0.00815   0.00193  -0.0972   0.7860   0.3658
  -0.500   0.3347   0.00815   0.00190  -0.0971   0.7796   0.3698
  -0.250   0.3618   0.00814   0.00186  -0.0970   0.7724   0.3734
   0.000   0.3888   0.00809   0.00184  -0.0969   0.7657   0.3775
   0.250   0.4157   0.00808   0.00183  -0.0968   0.7578   0.3821
   0.500   0.4424   0.00809   0.00182  -0.0966   0.7479   0.3866
   0.750   0.4660   0.00801   0.00169  -0.0955   0.7194   0.3911
   1.000   0.4909   0.00802   0.00168  -0.0949   0.6965   0.3961
   1.250   0.5153   0.00808   0.00164  -0.0941   0.6669   0.4008
   1.500   0.5380   0.00820   0.00165  -0.0931   0.6236   0.4057
   1.750   0.5516   0.00897   0.00179  -0.0903   0.4926   0.4103
   2.000   0.5557   0.01089   0.00245  -0.0865   0.2192   0.4140
   2.250   0.5700   0.01209   0.00305  -0.0843   0.0211   0.4189
   2.500   0.5952   0.01227   0.00336  -0.0838   0.0198   0.4256
   2.750   0.6192   0.01253   0.00382  -0.0830   0.0165   0.4331
   3.000   0.6421   0.01291   0.00436  -0.0820   0.0148   0.4424
   3.250   0.6629   0.01347   0.00509  -0.0805   0.0141   0.4548
   3.500   0.6824   0.01407   0.00591  -0.0788   0.0152   0.4762
   3.750   0.6985   0.01469   0.00693  -0.0764   0.0179   0.5633
   5.000   0.7978   0.00854   0.00216  -0.0688   0.0158   1.0000
   5.250   0.8234   0.00995   0.00360  -0.0685   0.0134   1.0000
   5.500   0.8527   0.01296   0.00660  -0.0690   0.0112   1.0000
   5.750   0.9030   0.02984   0.02343  -0.0720   0.0103   1.0000
   6.000   0.9239   0.03211   0.02594  -0.0703   0.0103   1.0000
   6.250   0.9430   0.03425   0.02832  -0.0685   0.0102   1.0000
   6.500   0.9610   0.03609   0.03040  -0.0664   0.0101   1.0000
   6.750   0.9821   0.03596   0.03051  -0.0645   0.0093   1.0000
   7.000   1.0025   0.03714   0.03190  -0.0626   0.0083   1.0000
   7.250   1.0187   0.03928   0.03428  -0.0603   0.0075   1.0000
   7.500   1.0324   0.04174   0.03697  -0.0580   0.0071   1.0000
   7.750   1.0433   0.04442   0.03988  -0.0554   0.0067   1.0000
   8.000   1.0518   0.04720   0.04288  -0.0528   0.0064   1.0000
   8.250   1.0577   0.05006   0.04596  -0.0501   0.0062   1.0000
   8.500   1.0613   0.05297   0.04908  -0.0474   0.0060   1.0000
   8.750   1.0613   0.05602   0.05232  -0.0444   0.0058   1.0000
   9.000   1.0587   0.05902   0.05549  -0.0414   0.0057   1.0000
   9.250   1.0532   0.06197   0.05861  -0.0383   0.0056   1.0000
   9.500   1.0422   0.06464   0.06142  -0.0346   0.0056   1.0000
   9.750   1.0275   0.06728   0.06419  -0.0309   0.0055   1.0000
  10.000   1.0122   0.07015   0.06719  -0.0281   0.0055   1.0000
  10.250   0.9957   0.07346   0.07063  -0.0261   0.0055   1.0000
  10.500   0.9787   0.07710   0.07439  -0.0251   0.0055   1.0000
  10.750   0.9604   0.08133   0.07874  -0.0250   0.0055   1.0000
  11.000   0.9423   0.08606   0.08360  -0.0260   0.0055   1.0000
  11.250   0.9236   0.09153   0.08918  -0.0280   0.0056   1.0000
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