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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 200,000
Max Cl/Cd: 66.1 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe147-il-200000-n5.txt
Download as CSV file: xf-goe147-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4549   0.09393   0.09066   0.0058   1.0000   0.0164
  -7.750  -0.4515   0.08997   0.08675   0.0036   1.0000   0.0161
  -7.500  -0.4486   0.08575   0.08257   0.0007   1.0000   0.0157
  -7.250  -0.4418   0.08049   0.07735  -0.0042   1.0000   0.0150
  -7.000  -0.4327   0.07408   0.07095  -0.0108   1.0000   0.0144
  -6.750  -0.4205   0.06519   0.06204  -0.0202   1.0000   0.0137
  -6.500  -0.4027   0.05455   0.05129  -0.0310   1.0000   0.0133
  -6.250  -0.3731   0.03593   0.03199  -0.0483   1.0000   0.0129
  -6.000  -0.3442   0.02688   0.02199  -0.0544   1.0000   0.0130
  -5.750  -0.3181   0.02276   0.01727  -0.0561   1.0000   0.0135
  -5.500  -0.2919   0.02092   0.01517  -0.0566   1.0000   0.0145
  -5.250  -0.2653   0.01966   0.01372  -0.0567   1.0000   0.0159
  -5.000  -0.2384   0.01825   0.01204  -0.0568   1.0000   0.0170
  -4.750  -0.2115   0.01697   0.01054  -0.0566   1.0000   0.0180
  -4.500  -0.1847   0.01598   0.00936  -0.0563   1.0000   0.0190
  -4.250  -0.1583   0.01504   0.00826  -0.0561   1.0000   0.0208
  -4.000  -0.1229   0.01412   0.00721  -0.0578   0.9870   0.0244
  -3.750  -0.0849   0.01341   0.00629  -0.0597   0.9642   0.0281
  -3.500  -0.0464   0.01254   0.00528  -0.0616   0.9299   0.0371
  -3.250  -0.0119   0.01222   0.00510  -0.0626   0.8856   0.0805
  -3.000   0.0162   0.01259   0.00510  -0.0617   0.8392   0.0990
  -2.750   0.0417   0.01285   0.00513  -0.0607   0.7961   0.1087
  -2.500   0.0674   0.01294   0.00502  -0.0599   0.7592   0.1174
  -2.250   0.0940   0.01294   0.00481  -0.0593   0.7283   0.1225
  -2.000   0.1210   0.01291   0.00453  -0.0588   0.7004   0.1263
  -1.750   0.1480   0.01269   0.00419  -0.0584   0.6752   0.1289
  -1.500   0.1753   0.01255   0.00391  -0.0580   0.6528   0.1298
  -1.250   0.2028   0.01244   0.00366  -0.0577   0.6329   0.1309
  -1.000   0.2304   0.01234   0.00345  -0.0575   0.6148   0.1320
  -0.750   0.2580   0.01227   0.00327  -0.0572   0.5976   0.1332
  -0.500   0.2857   0.01221   0.00311  -0.0570   0.5809   0.1346
  -0.250   0.3135   0.01216   0.00298  -0.0568   0.5649   0.1361
   0.000   0.3413   0.01214   0.00288  -0.0566   0.5490   0.1383
   0.250   0.3691   0.01213   0.00280  -0.0565   0.5318   0.1408
   0.500   0.3968   0.01212   0.00275  -0.0563   0.5130   0.1437
   0.750   0.4245   0.01215   0.00271  -0.0561   0.4930   0.1468
   1.000   0.4523   0.01218   0.00270  -0.0560   0.4709   0.1508
   1.250   0.4799   0.01223   0.00270  -0.0559   0.4470   0.1565
   1.500   0.5075   0.01230   0.00272  -0.0557   0.4203   0.1665
   1.750   0.5349   0.01242   0.00277  -0.0556   0.3914   0.1835
   2.000   0.5622   0.01256   0.00285  -0.0555   0.3657   0.2067
   2.250   0.5894   0.01271   0.00295  -0.0554   0.3445   0.2329
   2.500   0.6166   0.01281   0.00309  -0.0554   0.3273   0.2717
   3.250   0.6920   0.01192   0.00353  -0.0534   0.2924   1.0000
   3.500   0.7193   0.01217   0.00372  -0.0532   0.2828   1.0000
   3.750   0.7465   0.01244   0.00392  -0.0531   0.2733   1.0000
   4.000   0.7738   0.01267   0.00416  -0.0530   0.2641   1.0000
   4.250   0.8009   0.01295   0.00439  -0.0528   0.2556   1.0000
   4.500   0.8281   0.01320   0.00464  -0.0527   0.2470   1.0000
   4.750   0.8551   0.01348   0.00493  -0.0525   0.2392   1.0000
   5.000   0.8820   0.01376   0.00521  -0.0524   0.2310   1.0000
   5.250   0.9088   0.01405   0.00552  -0.0522   0.2233   1.0000
   5.500   0.9354   0.01437   0.00585  -0.0520   0.2151   1.0000
   5.750   0.9621   0.01467   0.00622  -0.0518   0.2073   1.0000
   6.000   0.9884   0.01503   0.00659  -0.0516   0.1996   1.0000
   6.250   1.0148   0.01537   0.00699  -0.0514   0.1921   1.0000
   6.500   1.0407   0.01577   0.00742  -0.0512   0.1854   1.0000
   6.750   1.0668   0.01614   0.00791  -0.0509   0.1793   1.0000
   7.000   1.0924   0.01656   0.00834  -0.0506   0.1714   1.0000
   7.250   1.1181   0.01694   0.00877  -0.0504   0.1609   1.0000
   7.500   1.1432   0.01737   0.00921  -0.0502   0.1474   1.0000
   7.750   1.1675   0.01793   0.00972  -0.0499   0.1318   1.0000
   8.000   1.1916   0.01854   0.01037  -0.0496   0.1175   1.0000
   8.250   1.2149   0.01928   0.01108  -0.0492   0.0886   1.0000
   8.500   1.2284   0.02172   0.01308  -0.0481   0.0259   1.0000
   8.750   1.2491   0.02287   0.01435  -0.0473   0.0198   1.0000
   9.000   1.2684   0.02417   0.01583  -0.0464   0.0165   1.0000
   9.250   1.2879   0.02532   0.01720  -0.0455   0.0150   1.0000
   9.500   1.3057   0.02661   0.01870  -0.0446   0.0138   1.0000
   9.750   1.3215   0.02803   0.02030  -0.0436   0.0126   1.0000
  10.000   1.3314   0.02999   0.02249  -0.0422   0.0114   1.0000
  10.250   1.3381   0.03204   0.02473  -0.0406   0.0108   1.0000
  10.500   1.3451   0.03388   0.02673  -0.0390   0.0104   1.0000
  10.750   1.3468   0.03588   0.02889  -0.0370   0.0101   1.0000
  11.000   1.3442   0.03819   0.03136  -0.0352   0.0099   1.0000
  11.250   1.3407   0.04104   0.03437  -0.0345   0.0097   1.0000
  11.500   1.3368   0.04443   0.03791  -0.0349   0.0095   1.0000
  11.750   1.3325   0.04824   0.04188  -0.0359   0.0093   1.0000
  12.000   1.3279   0.05235   0.04614  -0.0373   0.0091   1.0000
  12.250   1.3230   0.05663   0.05056  -0.0389   0.0089   1.0000
  12.500   1.3175   0.06106   0.05512  -0.0405   0.0088   1.0000
  12.750   1.3115   0.06559   0.05977  -0.0421   0.0086   1.0000
  13.000   1.3049   0.07022   0.06452  -0.0438   0.0084   1.0000
  13.250   1.2975   0.07504   0.06944  -0.0457   0.0082   1.0000
  13.500   1.2900   0.07986   0.07437  -0.0474   0.0081   1.0000
  13.750   1.2821   0.08477   0.07938  -0.0492   0.0079   1.0000
  14.000   1.2741   0.08970   0.08440  -0.0510   0.0078   1.0000
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