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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 200,000
Max Cl/Cd: 74.69 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe133-il-200000-n5.txt
Download as CSV file: xf-goe133-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3437   0.08654   0.08322  -0.0248   1.0000   0.0178
  -7.250  -0.3467   0.08406   0.08079  -0.0244   1.0000   0.0174
  -7.000  -0.3491   0.08139   0.07818  -0.0247   1.0000   0.0169
  -6.750  -0.3516   0.07864   0.07548  -0.0251   1.0000   0.0166
  -6.500  -0.3263   0.07327   0.07009  -0.0335   0.9948   0.0171
  -6.250  -0.2943   0.06710   0.06386  -0.0436   0.9879   0.0176
  -6.000  -0.2618   0.06113   0.05780  -0.0527   0.9812   0.0174
  -5.750  -0.2253   0.05477   0.05130  -0.0621   0.9762   0.0171
  -5.500  -0.1919   0.04854   0.04489  -0.0695   0.9689   0.0170
  -5.250  -0.1539   0.04171   0.03778  -0.0770   0.9639   0.0172
  -5.000  -0.1187   0.03316   0.02870  -0.0828   0.9560   0.0184
  -4.750  -0.0831   0.02723   0.02225  -0.0866   0.9512   0.0198
  -4.500  -0.0541   0.02379   0.01838  -0.0877   0.9428   0.0210
  -4.250  -0.0204   0.01918   0.01291  -0.0893   0.9372   0.0240
  -4.000   0.0086   0.01794   0.01140  -0.0896   0.9282   0.0266
  -3.750   0.0404   0.01702   0.01026  -0.0903   0.9210   0.0293
  -3.500   0.0690   0.01591   0.00882  -0.0902   0.9105   0.0335
  -3.250   0.0979   0.01562   0.00848  -0.0902   0.8997   0.0368
  -3.000   0.1274   0.01506   0.00767  -0.0902   0.8885   0.0414
  -2.750   0.1557   0.01438   0.00693  -0.0901   0.8765   0.0452
  -2.500   0.1839   0.01401   0.00645  -0.0899   0.8627   0.0495
  -2.250   0.2117   0.01356   0.00584  -0.0895   0.8470   0.0527
  -2.000   0.2390   0.01294   0.00513  -0.0892   0.8295   0.0560
  -1.750   0.2663   0.01251   0.00463  -0.0888   0.8108   0.0591
  -1.500   0.2935   0.01217   0.00419  -0.0883   0.7916   0.0616
  -1.250   0.3205   0.01190   0.00380  -0.0878   0.7713   0.0644
  -1.000   0.3475   0.01173   0.00349  -0.0873   0.7500   0.0675
  -0.750   0.3742   0.01152   0.00320  -0.0869   0.7286   0.0724
  -0.500   0.4009   0.01143   0.00300  -0.0865   0.7055   0.0770
  -0.250   0.4275   0.01140   0.00282  -0.0860   0.6806   0.0827
   0.000   0.4538   0.01137   0.00270  -0.0855   0.6526   0.0935
   0.500   0.5062   0.01116   0.00259  -0.0848   0.5975   0.2161
   1.000   0.5555   0.00963   0.00262  -0.0831   0.5585   1.0000
   1.250   0.5821   0.00984   0.00264  -0.0828   0.5412   1.0000
   1.500   0.6087   0.01005   0.00268  -0.0825   0.5249   1.0000
   1.750   0.6353   0.01026   0.00276  -0.0822   0.5101   1.0000
   2.000   0.6622   0.01045   0.00284  -0.0819   0.4982   1.0000
   2.250   0.6889   0.01066   0.00294  -0.0817   0.4872   1.0000
   2.500   0.7159   0.01084   0.00306  -0.0815   0.4760   1.0000
   2.750   0.7428   0.01103   0.00319  -0.0813   0.4656   1.0000
   3.000   0.7695   0.01123   0.00333  -0.0810   0.4558   1.0000
   3.250   0.7963   0.01142   0.00350  -0.0808   0.4453   1.0000
   3.500   0.8230   0.01162   0.00367  -0.0806   0.4349   1.0000
   3.750   0.8496   0.01183   0.00385  -0.0803   0.4241   1.0000
   4.000   0.8759   0.01205   0.00405  -0.0801   0.4125   1.0000
   4.250   0.9021   0.01227   0.00425  -0.0798   0.3980   1.0000
   4.500   0.9280   0.01251   0.00446  -0.0795   0.3799   1.0000
   4.750   0.9535   0.01278   0.00469  -0.0791   0.3570   1.0000
   5.000   0.9785   0.01310   0.00493  -0.0787   0.3319   1.0000
   5.250   1.0031   0.01347   0.00521  -0.0782   0.3058   1.0000
   5.500   1.0271   0.01391   0.00554  -0.0777   0.2803   1.0000
   5.750   1.0509   0.01439   0.00593  -0.0772   0.2589   1.0000
   6.000   1.0747   0.01486   0.00634  -0.0766   0.2424   1.0000
   6.250   1.0987   0.01531   0.00677  -0.0761   0.2301   1.0000
   6.500   1.1225   0.01577   0.00724  -0.0756   0.2201   1.0000
   6.750   1.1462   0.01622   0.00770  -0.0751   0.2099   1.0000
   7.000   1.1701   0.01665   0.00817  -0.0745   0.2006   1.0000
   7.250   1.1933   0.01713   0.00867  -0.0739   0.1919   1.0000
   7.500   1.2171   0.01754   0.00918  -0.0734   0.1831   1.0000
   7.750   1.2403   0.01800   0.00971  -0.0728   0.1745   1.0000
   8.000   1.2627   0.01852   0.01026  -0.0721   0.1631   1.0000
   8.250   1.2854   0.01900   0.01081  -0.0715   0.1468   1.0000
   8.500   1.3066   0.01962   0.01141  -0.0706   0.1169   1.0000
   8.750   1.3231   0.02071   0.01230  -0.0694   0.0918   1.0000
   9.000   1.3402   0.02171   0.01329  -0.0680   0.0823   1.0000
   9.250   1.3551   0.02286   0.01445  -0.0665   0.0742   1.0000
   9.500   1.3737   0.02359   0.01533  -0.0653   0.0677   1.0000
   9.750   1.3889   0.02459   0.01638  -0.0639   0.0619   1.0000
  10.000   1.4056   0.02539   0.01731  -0.0625   0.0569   1.0000
  10.250   1.4215   0.02622   0.01826  -0.0611   0.0516   1.0000
  10.500   1.4346   0.02719   0.01930  -0.0594   0.0467   1.0000
  10.750   1.4470   0.02806   0.02027  -0.0575   0.0411   1.0000
  11.000   1.4570   0.02912   0.02141  -0.0554   0.0354   1.0000
  11.250   1.4647   0.03038   0.02271  -0.0533   0.0288   1.0000
  11.500   1.4697   0.03189   0.02426  -0.0511   0.0229   1.0000
  11.750   1.4727   0.03361   0.02607  -0.0490   0.0194   1.0000
  12.000   1.4724   0.03573   0.02826  -0.0469   0.0172   1.0000
  12.250   1.4721   0.03798   0.03066  -0.0452   0.0158   1.0000
  12.500   1.4712   0.04045   0.03332  -0.0440   0.0148   1.0000
  12.750   1.4688   0.04325   0.03627  -0.0431   0.0138   1.0000
  13.000   1.4640   0.04651   0.03966  -0.0426   0.0130   1.0000
  13.250   1.4563   0.05036   0.04365  -0.0426   0.0124   1.0000
  13.500   1.4474   0.05460   0.04805  -0.0431   0.0119   1.0000
  13.750   1.4412   0.05867   0.05230  -0.0438   0.0116   1.0000
  14.000   1.4332   0.06314   0.05696  -0.0448   0.0113   1.0000
  14.250   1.4239   0.06794   0.06194  -0.0461   0.0111   1.0000
  14.500   1.4136   0.07300   0.06717  -0.0476   0.0109   1.0000
  14.750   1.4025   0.07830   0.07263  -0.0493   0.0107   1.0000
  15.000   1.3908   0.08383   0.07832  -0.0511   0.0105   1.0000
  15.250   1.3787   0.08952   0.08416  -0.0532   0.0103   1.0000
  15.500   1.3664   0.09537   0.09017  -0.0554   0.0102   1.0000
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