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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.2 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe137-il-1000000-n5.txt
Download as CSV file: xf-goe137-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4120   0.11137   0.10980  -0.0106   1.0000   0.0043
  -9.250  -0.5636   0.02140   0.01839  -0.0840   0.9568   0.0054
  -9.000  -0.5429   0.01856   0.01516  -0.0843   0.9489   0.0056
  -8.750  -0.5197   0.01697   0.01332  -0.0842   0.9402   0.0058
  -8.500  -0.4954   0.01579   0.01192  -0.0840   0.9316   0.0060
  -8.250  -0.4710   0.01465   0.01057  -0.0837   0.9223   0.0064
  -8.000  -0.4455   0.01379   0.00955  -0.0835   0.9120   0.0068
  -7.750  -0.4197   0.01310   0.00871  -0.0833   0.9003   0.0073
  -7.500  -0.3937   0.01251   0.00797  -0.0830   0.8864   0.0078
  -7.250  -0.3674   0.01199   0.00727  -0.0827   0.8703   0.0083
  -7.000  -0.3411   0.01151   0.00663  -0.0824   0.8510   0.0091
  -6.750  -0.3144   0.01112   0.00611  -0.0821   0.8278   0.0101
  -6.500  -0.2877   0.01081   0.00563  -0.0819   0.8010   0.0112
  -6.250  -0.2606   0.01056   0.00520  -0.0817   0.7740   0.0123
  -6.000  -0.2329   0.01058   0.00516  -0.0816   0.7494   0.0140
  -5.750  -0.2050   0.01057   0.00507  -0.0815   0.7295   0.0155
  -5.500  -0.1771   0.01046   0.00483  -0.0815   0.7129   0.0166
  -5.250  -0.1489   0.01049   0.00483  -0.0815   0.6988   0.0177
  -5.000  -0.1205   0.01059   0.00490  -0.0815   0.6860   0.0186
  -4.750  -0.0922   0.01062   0.00487  -0.0815   0.6739   0.0196
  -4.500  -0.0639   0.01059   0.00478  -0.0815   0.6621   0.0208
  -4.250  -0.0356   0.01052   0.00463  -0.0816   0.6514   0.0219
  -4.000  -0.0073   0.01045   0.00448  -0.0816   0.6417   0.0227
  -3.750   0.0210   0.01041   0.00438  -0.0816   0.6327   0.0232
  -3.500   0.0495   0.01037   0.00429  -0.0817   0.6249   0.0236
  -3.250   0.0779   0.01035   0.00420  -0.0817   0.6165   0.0238
  -3.000   0.1054   0.00946   0.00318  -0.0818   0.6068   0.0255
  -2.750   0.1336   0.00925   0.00289  -0.0818   0.5962   0.0265
  -2.500   0.1618   0.00908   0.00265  -0.0819   0.5848   0.0271
  -2.250   0.1901   0.00891   0.00242  -0.0819   0.5750   0.0275
  -2.000   0.2185   0.00877   0.00222  -0.0820   0.5667   0.0279
  -1.750   0.2469   0.00864   0.00203  -0.0820   0.5573   0.0282
  -1.500   0.2753   0.00852   0.00186  -0.0821   0.5480   0.0285
  -1.250   0.3037   0.00843   0.00171  -0.0822   0.5386   0.0287
  -1.000   0.3321   0.00836   0.00158  -0.0822   0.5273   0.0291
  -0.750   0.3604   0.00832   0.00148  -0.0823   0.5139   0.0297
  -0.500   0.3887   0.00830   0.00138  -0.0824   0.4995   0.0300
  -0.250   0.4169   0.00829   0.00130  -0.0824   0.4849   0.0303
   0.000   0.4451   0.00830   0.00125  -0.0825   0.4713   0.0309
   0.250   0.4733   0.00832   0.00121  -0.0825   0.4586   0.0319
   0.500   0.5014   0.00837   0.00120  -0.0826   0.4432   0.0333
   0.750   0.5294   0.00843   0.00120  -0.0826   0.4291   0.0351
   1.000   0.5575   0.00847   0.00121  -0.0827   0.4174   0.0439
   1.250   0.5855   0.00841   0.00126  -0.0828   0.4056   0.1065
   1.500   0.6134   0.00846   0.00132  -0.0829   0.3936   0.1291
   1.750   0.6414   0.00850   0.00138  -0.0830   0.3821   0.1505
   2.000   0.6694   0.00850   0.00145  -0.0831   0.3723   0.1919
   2.250   0.6972   0.00839   0.00156  -0.0833   0.3630   0.3086
   2.750   0.7488   0.00710   0.00182  -0.0828   0.3440   1.0000
   3.000   0.7764   0.00726   0.00192  -0.0829   0.3331   1.0000
   3.250   0.8040   0.00742   0.00202  -0.0829   0.3222   1.0000
   3.500   0.8313   0.00763   0.00215  -0.0829   0.3067   1.0000
   3.750   0.8583   0.00786   0.00229  -0.0828   0.2869   1.0000
   4.000   0.8851   0.00811   0.00245  -0.0828   0.2670   1.0000
   4.250   0.9111   0.00848   0.00265  -0.0826   0.2357   1.0000
   4.500   0.9347   0.00919   0.00305  -0.0822   0.1769   1.0000
   4.750   0.9612   0.00947   0.00326  -0.0821   0.1661   1.0000
   5.000   0.9878   0.00971   0.00348  -0.0820   0.1586   1.0000
   5.250   1.0144   0.00994   0.00369  -0.0819   0.1515   1.0000
   5.500   1.0411   0.01015   0.00388  -0.0818   0.1447   1.0000
   5.750   1.0673   0.01043   0.00412  -0.0817   0.1345   1.0000
   6.000   1.0896   0.01119   0.00457  -0.0811   0.0828   1.0000
   6.250   1.1134   0.01175   0.00503  -0.0806   0.0592   1.0000
   6.500   1.1339   0.01273   0.00576  -0.0797   0.0154   1.0000
   6.750   1.1589   0.01308   0.00614  -0.0794   0.0114   1.0000
   7.000   1.1841   0.01339   0.00648  -0.0791   0.0105   1.0000
   7.250   1.2087   0.01375   0.00687  -0.0787   0.0093   1.0000
   7.500   1.2326   0.01419   0.00733  -0.0782   0.0080   1.0000
   7.750   1.2566   0.01459   0.00777  -0.0778   0.0073   1.0000
   8.000   1.2804   0.01498   0.00820  -0.0773   0.0067   1.0000
   8.250   1.3037   0.01542   0.00866  -0.0768   0.0061   1.0000
   8.500   1.3263   0.01591   0.00918  -0.0762   0.0056   1.0000
   8.750   1.3473   0.01654   0.00986  -0.0753   0.0051   1.0000
   9.000   1.3693   0.01704   0.01040  -0.0746   0.0049   1.0000
   9.250   1.3906   0.01756   0.01098  -0.0738   0.0047   1.0000
   9.500   1.4114   0.01811   0.01158  -0.0729   0.0043   1.0000
   9.750   1.4316   0.01867   0.01218  -0.0720   0.0041   1.0000
  10.000   1.4509   0.01926   0.01282  -0.0710   0.0038   1.0000
  10.250   1.4682   0.01999   0.01359  -0.0697   0.0036   1.0000
  10.500   1.4816   0.02098   0.01467  -0.0678   0.0034   1.0000
  10.750   1.4965   0.02172   0.01548  -0.0662   0.0033   1.0000
  11.000   1.5073   0.02254   0.01637  -0.0639   0.0032   1.0000
  11.250   1.5170   0.02346   0.01737  -0.0616   0.0031   1.0000
  11.500   1.5257   0.02450   0.01852  -0.0594   0.0030   1.0000
  11.750   1.5331   0.02570   0.01980  -0.0573   0.0029   1.0000
  12.000   1.5399   0.02703   0.02122  -0.0554   0.0028   1.0000
  12.250   1.5457   0.02853   0.02281  -0.0537   0.0028   1.0000
  12.500   1.5511   0.03018   0.02456  -0.0522   0.0027   1.0000
  12.750   1.5549   0.03208   0.02655  -0.0510   0.0026   1.0000
  13.000   1.5585   0.03415   0.02872  -0.0500   0.0026   1.0000
  13.250   1.5615   0.03640   0.03107  -0.0493   0.0025   1.0000
  13.500   1.5632   0.03895   0.03371  -0.0489   0.0024   1.0000
  13.750   1.5639   0.04169   0.03654  -0.0486   0.0024   1.0000
  14.000   1.5632   0.04469   0.03965  -0.0486   0.0024   1.0000
  14.250   1.5608   0.04799   0.04305  -0.0487   0.0023   1.0000
  14.500   1.5561   0.05162   0.04678  -0.0489   0.0023   1.0000
  14.750   1.5496   0.05557   0.05084  -0.0493   0.0022   1.0000
  15.000   1.5406   0.05993   0.05534  -0.0499   0.0022   1.0000
  15.250   1.5295   0.06472   0.06025  -0.0508   0.0022   1.0000
  15.500   1.5164   0.06998   0.06564  -0.0519   0.0021   1.0000
  15.750   1.5020   0.07557   0.07136  -0.0533   0.0021   1.0000
  16.000   1.4876   0.08134   0.07725  -0.0549   0.0021   1.0000
  16.250   1.4790   0.08637   0.08239  -0.0564   0.0021   1.0000
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