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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 200,000
Max Cl/Cd: 78.36 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe137-il-200000.txt
Download as CSV file: xf-goe137-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3442   0.09320   0.08988  -0.0236   1.0000   0.0387
  -7.750  -0.3462   0.09082   0.08758  -0.0276   1.0000   0.0397
  -7.500  -0.3420   0.08791   0.08472  -0.0339   1.0000   0.0402
  -7.250  -0.3372   0.08475   0.08159  -0.0378   1.0000   0.0404
  -7.000  -0.3334   0.08162   0.07847  -0.0400   1.0000   0.0406
  -6.750  -0.3400   0.07630   0.07323  -0.0394   1.0000   0.0412
  -6.500  -0.3425   0.07357   0.07056  -0.0358   1.0000   0.0419
  -6.250  -0.3442   0.07160   0.06864  -0.0331   1.0000   0.0427
  -6.000  -0.3375   0.06915   0.06621  -0.0329   0.9986   0.0438
  -5.750  -0.3001   0.06453   0.06151  -0.0408   0.9932   0.0481
  -5.500  -0.1754   0.03920   0.03619  -0.0630   0.9700   0.0572
  -5.250  -0.1442   0.03452   0.03137  -0.0691   0.9606   0.0629
  -5.000  -0.1556   0.04695   0.04296  -0.0732   0.9725   0.0664
  -4.750  -0.1287   0.04278   0.03900  -0.0755   0.9676   0.0694
  -4.500  -0.0554   0.02188   0.01821  -0.0812   0.9299   0.0839
  -4.250  -0.0281   0.01859   0.01458  -0.0834   0.9160   0.0950
  -4.000  -0.0070   0.01679   0.01276  -0.0829   0.9014   0.1003
  -3.750   0.0160   0.01459   0.01033  -0.0832   0.8866   0.1118
  -3.500   0.0398   0.01267   0.00812  -0.0833   0.8719   0.1246
  -3.250   0.0630   0.01128   0.00659  -0.0828   0.8576   0.1319
  -3.000   0.1090   0.01909   0.01232  -0.0881   0.8847   0.0657
  -2.750   0.1353   0.01724   0.01016  -0.0873   0.8694   0.0648
  -2.500   0.1618   0.01602   0.00866  -0.0864   0.8540   0.0646
  -2.250   0.1883   0.01517   0.00757  -0.0856   0.8387   0.0652
  -2.000   0.2147   0.01435   0.00657  -0.0849   0.8236   0.0671
  -1.750   0.2411   0.01357   0.00570  -0.0842   0.8093   0.0684
  -1.500   0.2676   0.01304   0.00511  -0.0836   0.7955   0.0703
  -1.250   0.2945   0.01266   0.00466  -0.0831   0.7820   0.0732
  -1.000   0.3215   0.01238   0.00431  -0.0826   0.7689   0.0769
  -0.750   0.3487   0.01213   0.00404  -0.0823   0.7564   0.0847
  -0.500   0.3760   0.01193   0.00385  -0.0819   0.7442   0.1014
  -0.250   0.4028   0.01148   0.00371  -0.0817   0.7323   0.2059
   0.000   0.4305   0.00942   0.00366  -0.0813   0.7208   1.0000
   0.250   0.4576   0.00956   0.00357  -0.0809   0.7081   1.0000
   0.500   0.4847   0.00969   0.00353  -0.0806   0.6955   1.0000
   0.750   0.5118   0.00983   0.00352  -0.0803   0.6833   1.0000
   1.000   0.5389   0.00998   0.00352  -0.0800   0.6713   1.0000
   1.250   0.5660   0.01013   0.00353  -0.0797   0.6593   1.0000
   1.500   0.5930   0.01028   0.00354  -0.0793   0.6477   1.0000
   1.750   0.6201   0.01041   0.00360  -0.0791   0.6351   1.0000
   2.000   0.6473   0.01056   0.00368  -0.0789   0.6231   1.0000
   2.250   0.6744   0.01071   0.00376  -0.0787   0.6114   1.0000
   2.500   0.7013   0.01087   0.00383  -0.0784   0.5992   1.0000
   2.750   0.7283   0.01103   0.00390  -0.0781   0.5872   1.0000
   3.000   0.7552   0.01118   0.00402  -0.0779   0.5751   1.0000
   3.250   0.7822   0.01134   0.00416  -0.0777   0.5628   1.0000
   3.500   0.8091   0.01151   0.00430  -0.0775   0.5505   1.0000
   3.750   0.8358   0.01168   0.00445  -0.0772   0.5376   1.0000
   4.000   0.8624   0.01187   0.00460  -0.0770   0.5256   1.0000
   4.250   0.8890   0.01207   0.00476  -0.0767   0.5134   1.0000
   4.500   0.9154   0.01227   0.00493  -0.0764   0.5012   1.0000
   4.750   0.9418   0.01248   0.00517  -0.0762   0.4887   1.0000
   5.000   0.9681   0.01270   0.00540  -0.0759   0.4762   1.0000
   5.250   0.9941   0.01293   0.00564  -0.0756   0.4630   1.0000
   5.500   1.0199   0.01318   0.00591  -0.0752   0.4497   1.0000
   5.750   1.0456   0.01345   0.00619  -0.0749   0.4366   1.0000
   6.000   1.0707   0.01371   0.00646  -0.0744   0.4207   1.0000
   6.250   1.0947   0.01400   0.00669  -0.0738   0.4000   1.0000
   6.500   1.1190   0.01428   0.00702  -0.0733   0.3783   1.0000
   6.750   1.1427   0.01463   0.00735  -0.0727   0.3578   1.0000
   7.000   1.1656   0.01502   0.00771  -0.0720   0.3298   1.0000
   7.250   1.1882   0.01547   0.00812  -0.0713   0.3018   1.0000
   7.500   1.2103   0.01599   0.00862  -0.0705   0.2724   1.0000
   7.750   1.2307   0.01668   0.00916  -0.0696   0.2343   1.0000
   8.000   1.2479   0.01769   0.00991  -0.0684   0.1931   1.0000
   8.250   1.2644   0.01879   0.01083  -0.0670   0.1621   1.0000
   8.500   1.2792   0.02007   0.01179  -0.0655   0.0936   1.0000
   8.750   1.2839   0.02231   0.01355  -0.0627   0.0418   1.0000
   9.000   1.2966   0.02366   0.01489  -0.0608   0.0327   1.0000
   9.250   1.3080   0.02503   0.01636  -0.0586   0.0293   1.0000
   9.500   1.3197   0.02624   0.01774  -0.0566   0.0279   1.0000
   9.750   1.3267   0.02756   0.01923  -0.0539   0.0268   1.0000
  10.000   1.3302   0.02907   0.02088  -0.0510   0.0260   1.0000
  10.250   1.3321   0.03082   0.02275  -0.0484   0.0253   1.0000
  10.500   1.3325   0.03282   0.02486  -0.0461   0.0248   1.0000
  10.750   1.3319   0.03508   0.02723  -0.0441   0.0241   1.0000
  11.000   1.3298   0.03766   0.02990  -0.0423   0.0234   1.0000
  11.250   1.3264   0.04057   0.03288  -0.0405   0.0227   1.0000
  11.500   1.3292   0.04303   0.03542  -0.0389   0.0222   1.0000
  11.750   1.3353   0.04520   0.03772  -0.0376   0.0219   1.0000
  12.000   1.3425   0.04739   0.04002  -0.0362   0.0217   1.0000
  12.250   1.3508   0.04961   0.04236  -0.0347   0.0216   1.0000
  12.500   1.3595   0.05194   0.04484  -0.0332   0.0215   1.0000
  12.750   1.3676   0.05450   0.04757  -0.0318   0.0214   1.0000
  13.000   1.3735   0.05741   0.05070  -0.0305   0.0215   1.0000
  13.250   1.3766   0.06071   0.05423  -0.0294   0.0216   1.0000
  13.500   1.3765   0.06447   0.05822  -0.0285   0.0218   1.0000
  13.750   1.3732   0.06871   0.06269  -0.0279   0.0220   1.0000
  14.000   1.3667   0.07333   0.06754  -0.0275   0.0222   1.0000
  14.250   1.3605   0.07836   0.07280  -0.0273   0.0224   1.0000
  14.500   1.3480   0.08295   0.07760  -0.0281   0.0225   1.0000
  14.750   1.3342   0.08779   0.08265  -0.0294   0.0225   1.0000
  15.000   1.3213   0.09259   0.08764  -0.0311   0.0226   1.0000
  15.250   1.3058   0.09801   0.09325  -0.0334   0.0227   1.0000
  15.500   1.2911   0.10354   0.09897  -0.0361   0.0228   1.0000
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