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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 500,000
Max Cl/Cd: 86.79 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe147-il-500000.txt
Download as CSV file: xf-goe147-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.6) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4952   0.09535   0.09327   0.0096   1.0000   0.0201
  -8.000  -0.4995   0.08937   0.08734   0.0064   1.0000   0.0204
  -7.750  -0.4960   0.08580   0.08378   0.0050   1.0000   0.0210
  -7.500  -0.4851   0.08295   0.08094   0.0030   1.0000   0.0214
  -7.250  -0.4730   0.07972   0.07771   0.0000   1.0000   0.0221
  -7.000  -0.4595   0.07588   0.07388  -0.0041   1.0000   0.0229
  -6.750  -0.4440   0.07125   0.06923  -0.0095   1.0000   0.0240
  -6.500  -0.4185   0.06457   0.06250  -0.0191   1.0000   0.0267
  -6.250  -0.4019   0.02867   0.02560  -0.0471   1.0000   0.0179
  -6.000  -0.3764   0.02056   0.01640  -0.0503   1.0000   0.0168
  -5.750  -0.3495   0.01798   0.01337  -0.0506   1.0000   0.0169
  -5.500  -0.3222   0.01635   0.01148  -0.0507   1.0000   0.0174
  -5.250  -0.2947   0.01509   0.01001  -0.0506   1.0000   0.0182
  -5.000  -0.2670   0.01402   0.00877  -0.0504   1.0000   0.0189
  -4.750  -0.2394   0.01323   0.00783  -0.0502   1.0000   0.0196
  -4.500  -0.2120   0.01204   0.00648  -0.0501   1.0000   0.0211
  -4.250  -0.1849   0.01123   0.00563  -0.0499   1.0000   0.0229
  -4.000  -0.1577   0.01065   0.00500  -0.0496   1.0000   0.0245
  -3.750  -0.1240   0.01014   0.00443  -0.0506   0.9911   0.0265
  -3.500  -0.0824   0.00938   0.00358  -0.0533   0.9554   0.0312
  -3.250  -0.0515   0.00905   0.00306  -0.0534   0.9020   0.0374
  -3.000  -0.0269   0.00897   0.00305  -0.0520   0.8541   0.0888
  -2.750  -0.0009   0.00953   0.00344  -0.0511   0.8120   0.1013
  -2.500   0.0258   0.00973   0.00341  -0.0505   0.7755   0.1072
  -2.250   0.0529   0.00978   0.00335  -0.0501   0.7408   0.1122
  -2.000   0.0804   0.00997   0.00336  -0.0497   0.7078   0.1172
  -1.750   0.1080   0.00989   0.00312  -0.0495   0.6784   0.1206
  -1.500   0.1357   0.00977   0.00290  -0.0493   0.6528   0.1242
  -1.250   0.1636   0.00977   0.00280  -0.0491   0.6300   0.1276
  -1.000   0.1916   0.00973   0.00265  -0.0490   0.6088   0.1296
  -0.750   0.2198   0.00966   0.00247  -0.0488   0.5901   0.1304
  -0.500   0.2480   0.00960   0.00233  -0.0487   0.5737   0.1313
  -0.250   0.2762   0.00956   0.00221  -0.0486   0.5582   0.1322
   0.250   0.3327   0.00942   0.00196  -0.0485   0.5257   0.1358
   0.500   0.3611   0.00938   0.00189  -0.0484   0.5087   0.1378
   0.750   0.3894   0.00937   0.00184  -0.0483   0.4904   0.1398
   1.000   0.4176   0.00940   0.00180  -0.0483   0.4689   0.1421
   1.250   0.4458   0.00946   0.00177  -0.0482   0.4398   0.1446
   1.500   0.4737   0.00958   0.00176  -0.0481   0.4021   0.1478
   1.750   0.5016   0.00973   0.00181  -0.0481   0.3688   0.1548
   2.000   0.5295   0.00987   0.00191  -0.0481   0.3441   0.1698
   2.250   0.5575   0.00997   0.00203  -0.0481   0.3265   0.2067
   2.500   0.5855   0.01001   0.00215  -0.0482   0.3126   0.2544
   2.750   0.6065   0.00841   0.00229  -0.0468   0.3021   1.0000
   3.000   0.6344   0.00862   0.00240  -0.0467   0.2918   1.0000
   3.250   0.6624   0.00880   0.00252  -0.0467   0.2822   1.0000
   3.500   0.6904   0.00897   0.00265  -0.0466   0.2737   1.0000
   3.750   0.7182   0.00919   0.00281  -0.0466   0.2651   1.0000
   4.000   0.7462   0.00934   0.00295  -0.0465   0.2572   1.0000
   4.250   0.7739   0.00955   0.00312  -0.0464   0.2492   1.0000
   4.500   0.8018   0.00972   0.00329  -0.0463   0.2410   1.0000
   4.750   0.8294   0.00993   0.00347  -0.0463   0.2328   1.0000
   5.000   0.8570   0.01015   0.00366  -0.0462   0.2235   1.0000
   5.250   0.8846   0.01035   0.00386  -0.0461   0.2140   1.0000
   5.500   0.9120   0.01059   0.00410  -0.0460   0.2035   1.0000
   5.750   0.9391   0.01087   0.00434  -0.0459   0.1915   1.0000
   6.000   0.9661   0.01117   0.00459  -0.0458   0.1786   1.0000
   6.250   0.9930   0.01147   0.00484  -0.0457   0.1656   1.0000
   6.500   1.0199   0.01177   0.00512  -0.0456   0.1554   1.0000
   6.750   1.0467   0.01206   0.00543  -0.0454   0.1485   1.0000
   7.000   1.0729   0.01244   0.00576  -0.0453   0.1395   1.0000
   7.250   1.0996   0.01272   0.00607  -0.0451   0.1325   1.0000
   7.500   1.1258   0.01309   0.00646  -0.0450   0.1239   1.0000
   7.750   1.1515   0.01351   0.00685  -0.0448   0.1083   1.0000
   8.000   1.1699   0.01548   0.00831  -0.0440   0.0290   1.0000
   8.250   1.1940   0.01627   0.00920  -0.0435   0.0233   1.0000
   8.500   1.2162   0.01741   0.01046  -0.0429   0.0197   1.0000
   8.750   1.2398   0.01815   0.01131  -0.0424   0.0183   1.0000
   9.000   1.2628   0.01894   0.01218  -0.0419   0.0167   1.0000
   9.250   1.2841   0.01996   0.01330  -0.0412   0.0154   1.0000
   9.500   1.3000   0.02174   0.01524  -0.0401   0.0143   1.0000
   9.750   1.3173   0.02316   0.01680  -0.0390   0.0138   1.0000
  10.000   1.3356   0.02431   0.01808  -0.0381   0.0133   1.0000
  10.250   1.3519   0.02562   0.01952  -0.0369   0.0128   1.0000
  10.500   1.3672   0.02696   0.02096  -0.0358   0.0122   1.0000
  10.750   1.3814   0.02829   0.02238  -0.0346   0.0116   1.0000
  11.000   1.3931   0.02975   0.02392  -0.0334   0.0110   1.0000
  11.250   1.3992   0.03163   0.02589  -0.0317   0.0107   1.0000
  11.500   1.3958   0.03392   0.02829  -0.0290   0.0104   1.0000
  11.750   1.3885   0.03684   0.03134  -0.0270   0.0102   1.0000
  12.000   1.3795   0.04058   0.03520  -0.0258   0.0100   1.0000
  12.250   1.3788   0.04358   0.03835  -0.0257   0.0099   1.0000
  12.500   1.3793   0.04665   0.04158  -0.0264   0.0098   1.0000
  12.750   1.3785   0.05007   0.04515  -0.0273   0.0097   1.0000
  13.000   1.3759   0.05385   0.04908  -0.0285   0.0096   1.0000
  13.250   1.3719   0.05794   0.05332  -0.0298   0.0096   1.0000
  13.500   1.3663   0.06232   0.05785  -0.0314   0.0095   1.0000
  13.750   1.3591   0.06700   0.06268  -0.0331   0.0094   1.0000
  14.000   1.3503   0.07198   0.06781  -0.0351   0.0093   1.0000
  14.250   1.3400   0.07726   0.07324  -0.0372   0.0093   1.0000
  14.500   1.3285   0.08285   0.07898  -0.0396   0.0093   1.0000
  14.750   1.3157   0.08879   0.08507  -0.0423   0.0092   1.0000
  15.000   1.3024   0.09503   0.09145  -0.0452   0.0093   1.0000
  15.250   1.2885   0.10163   0.09820  -0.0485   0.0093   1.0000
  15.500   1.2743   0.10862   0.10533  -0.0522   0.0093   1.0000
  15.750   1.2596   0.11594   0.11280  -0.0561   0.0093   1.0000
  16.000   1.2446   0.12350   0.12050  -0.0603   0.0094   1.0000
  16.250   1.2291   0.13148   0.12861  -0.0648   0.0094   1.0000
  16.500   1.2137   0.13971   0.13697  -0.0696   0.0095   1.0000
  16.750   1.1979   0.14827   0.14566  -0.0747   0.0096   1.0000
  17.000   1.1817   0.15731   0.15481  -0.0802   0.0097   1.0000
  17.250   1.1644   0.16700   0.16461  -0.0860   0.0098   1.0000
  17.500   0.9466   0.14558   0.14319  -0.0533   0.0102   1.0000
  17.750   0.9306   0.15171   0.14945  -0.0570   0.0104   1.0000
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