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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 100,000
Max Cl/Cd: 49.93 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe147-il-100000-n5.txt
Download as CSV file: xf-goe147-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4606   0.11440   0.10965   0.0127   1.0000   0.0463
  -8.750  -0.4555   0.11079   0.10607   0.0111   1.0000   0.0459
  -8.500  -0.4597   0.10402   0.09933   0.0057   1.0000   0.0287
  -8.250  -0.4522   0.10046   0.09579   0.0053   1.0000   0.0278
  -8.000  -0.4469   0.09681   0.09219   0.0039   1.0000   0.0271
  -7.750  -0.4425   0.09311   0.08854   0.0020   1.0000   0.0266
  -7.500  -0.4386   0.08935   0.08483  -0.0004   1.0000   0.0264
  -7.250  -0.4315   0.08516   0.08069  -0.0041   1.0000   0.0265
  -7.000  -0.4220   0.08065   0.07621  -0.0085   1.0000   0.0267
  -6.750  -0.4101   0.07587   0.07145  -0.0133   1.0000   0.0269
  -6.500  -0.3959   0.07078   0.06636  -0.0185   1.0000   0.0269
  -6.250  -0.3793   0.06536   0.06092  -0.0240   1.0000   0.0266
  -6.000  -0.3598   0.05949   0.05499  -0.0298   1.0000   0.0263
  -5.750  -0.3369   0.05283   0.04820  -0.0361   1.0000   0.0261
  -5.500  -0.3093   0.04386   0.03894  -0.0439   1.0000   0.0259
  -5.250  -0.2746   0.02972   0.02366  -0.0536   1.0000   0.0259
  -5.000  -0.2459   0.02538   0.01853  -0.0555   1.0000   0.0279
  -4.750  -0.2183   0.02283   0.01544  -0.0561   1.0000   0.0298
  -4.500  -0.1918   0.02084   0.01318  -0.0563   1.0000   0.0319
  -4.250  -0.1651   0.01946   0.01156  -0.0562   1.0000   0.0348
  -4.000  -0.1385   0.01826   0.01010  -0.0560   1.0000   0.0400
  -3.750  -0.1123   0.01714   0.00894  -0.0557   1.0000   0.0470
  -3.500  -0.0867   0.01662   0.00861  -0.0554   1.0000   0.0628
  -3.250  -0.0618   0.01697   0.00881  -0.0545   1.0000   0.0944
  -3.000  -0.0227   0.01733   0.00902  -0.0570   0.9840   0.1177
  -2.750   0.0180   0.01756   0.00915  -0.0596   0.9607   0.1363
  -2.500   0.0587   0.01748   0.00894  -0.0621   0.9298   0.1480
  -2.250   0.0978   0.01702   0.00813  -0.0638   0.8922   0.1538
  -2.000   0.1295   0.01657   0.00749  -0.0639   0.8527   0.1555
  -1.750   0.1574   0.01625   0.00697  -0.0632   0.8188   0.1570
  -1.500   0.1842   0.01599   0.00654  -0.0624   0.7881   0.1587
  -1.250   0.2106   0.01578   0.00615  -0.0616   0.7595   0.1606
  -1.000   0.2372   0.01559   0.00580  -0.0609   0.7329   0.1631
  -0.750   0.2639   0.01546   0.00549  -0.0602   0.7078   0.1666
  -0.500   0.2905   0.01532   0.00526  -0.0596   0.6848   0.1698
  -0.250   0.3170   0.01520   0.00506  -0.0590   0.6628   0.1729
   0.000   0.3436   0.01512   0.00486  -0.0584   0.6427   0.1766
   0.250   0.3705   0.01507   0.00469  -0.0578   0.6227   0.1812
   0.500   0.3973   0.01502   0.00460  -0.0573   0.6035   0.1865
   0.750   0.4244   0.01503   0.00450  -0.0569   0.5846   0.1949
   1.000   0.4515   0.01503   0.00445  -0.0565   0.5657   0.2059
   1.250   0.4788   0.01503   0.00442  -0.0562   0.5466   0.2231
   1.500   0.5060   0.01500   0.00443  -0.0559   0.5275   0.2515
   1.750   0.5330   0.01486   0.00447  -0.0558   0.5078   0.3214
   2.250   0.5823   0.01374   0.00450  -0.0537   0.4635   1.0000
   2.500   0.6092   0.01398   0.00459  -0.0534   0.4372   1.0000
   2.750   0.6358   0.01425   0.00468  -0.0531   0.4099   1.0000
   3.000   0.6622   0.01457   0.00480  -0.0527   0.3837   1.0000
   3.500   0.7148   0.01530   0.00522  -0.0521   0.3438   1.0000
   3.750   0.7412   0.01568   0.00550  -0.0519   0.3303   1.0000
   4.250   0.7941   0.01645   0.00620  -0.0514   0.3071   1.0000
   4.500   0.8205   0.01685   0.00658  -0.0511   0.2968   1.0000
   4.750   0.8465   0.01729   0.00698  -0.0508   0.2874   1.0000
   5.000   0.8728   0.01769   0.00745  -0.0506   0.2773   1.0000
   5.250   0.8988   0.01814   0.00792  -0.0503   0.2682   1.0000
   5.500   0.9246   0.01860   0.00839  -0.0500   0.2592   1.0000
   5.750   0.9506   0.01905   0.00896  -0.0497   0.2499   1.0000
   6.000   0.9759   0.01957   0.00947  -0.0493   0.2418   1.0000
   6.250   1.0016   0.02006   0.01008  -0.0490   0.2329   1.0000
   6.500   1.0267   0.02062   0.01068  -0.0487   0.2258   1.0000
   6.750   1.0521   0.02118   0.01141  -0.0483   0.2185   1.0000
   7.000   1.0768   0.02181   0.01207  -0.0479   0.2133   1.0000
   7.250   1.1020   0.02246   0.01292  -0.0475   0.2076   1.0000
   7.500   1.1268   0.02313   0.01374  -0.0471   0.2029   1.0000
   7.750   1.1511   0.02379   0.01445  -0.0467   0.1982   1.0000
   8.000   1.1749   0.02412   0.01507  -0.0463   0.1866   1.0000
   8.250   1.1979   0.02427   0.01537  -0.0459   0.1670   1.0000
   8.500   1.2209   0.02470   0.01592  -0.0456   0.1480   1.0000
   8.750   1.2421   0.02548   0.01669  -0.0451   0.1200   1.0000
   9.000   1.2534   0.02796   0.01864  -0.0442   0.0443   1.0000
   9.250   1.2642   0.03051   0.02127  -0.0428   0.0325   1.0000
   9.500   1.2763   0.03261   0.02363  -0.0415   0.0282   1.0000
   9.750   1.2832   0.03514   0.02637  -0.0401   0.0257   1.0000
  10.000   1.2920   0.03713   0.02866  -0.0388   0.0238   1.0000
  10.250   1.2964   0.03940   0.03118  -0.0374   0.0221   1.0000
  10.500   1.2949   0.04189   0.03390  -0.0358   0.0209   1.0000
  10.750   1.2879   0.04485   0.03714  -0.0346   0.0203   1.0000
  11.000   1.2789   0.04864   0.04113  -0.0350   0.0199   1.0000
  11.250   1.2685   0.05331   0.04601  -0.0368   0.0196   1.0000
  11.500   1.2571   0.05873   0.05162  -0.0396   0.0194   1.0000
  11.750   1.2447   0.06461   0.05767  -0.0426   0.0192   1.0000
  12.000   1.2319   0.07063   0.06385  -0.0456   0.0191   1.0000
  12.250   1.2196   0.07656   0.06992  -0.0483   0.0189   1.0000
  12.500   1.2087   0.08218   0.07565  -0.0505   0.0188   1.0000
  12.750   1.2002   0.08724   0.08081  -0.0523   0.0185   1.0000
  13.000   1.1944   0.09159   0.08522  -0.0533   0.0182   1.0000
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