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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 200,000
Max Cl/Cd: 78.03 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe144-il-200000-n5.txt
Download as CSV file: xf-goe144-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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  -0.3369   0.09082   0.08748  -0.0261   1.0000   0.0160
  -7.750  -0.3427   0.08816   0.08489  -0.0253   1.0000   0.0159
  -7.500  -0.3529   0.08590   0.08271  -0.0236   1.0000   0.0157
  -7.250  -0.3641   0.08385   0.08074  -0.0217   1.0000   0.0157
  -7.000  -0.3610   0.07984   0.07677  -0.0245   0.9981   0.0156
  -6.750  -0.3387   0.07419   0.07110  -0.0327   0.9924   0.0158
  -6.500  -0.3136   0.06831   0.06519  -0.0414   0.9868   0.0162
  -6.250  -0.2878   0.06291   0.05974  -0.0494   0.9801   0.0177
  -5.750  -0.2140   0.02530   0.02057  -0.0884   0.9653   0.0201
  -5.500  -0.1865   0.02130   0.01583  -0.0902   0.9590   0.0216
  -5.250  -0.1538   0.01975   0.01408  -0.0921   0.9549   0.0248
  -5.000  -0.1228   0.01821   0.01217  -0.0931   0.9497   0.0279
  -4.750  -0.0912   0.01699   0.01053  -0.0940   0.9442   0.0310
  -4.500  -0.0563   0.01564   0.00896  -0.0956   0.9402   0.0350
  -4.250  -0.0254   0.01496   0.00811  -0.0962   0.9335   0.0387
  -4.000   0.0096   0.01424   0.00718  -0.0976   0.9278   0.0420
  -3.750   0.0444   0.01364   0.00651  -0.0989   0.9218   0.0463
  -3.500   0.0777   0.01319   0.00597  -0.0998   0.9139   0.0506
  -3.250   0.1124   0.01276   0.00548  -0.1010   0.9061   0.0563
  -3.000   0.1469   0.01240   0.00500  -0.1021   0.8970   0.0661
  -2.750   0.1783   0.01215   0.00460  -0.1025   0.8852   0.0759
  -2.500   0.2088   0.01184   0.00426  -0.1029   0.8718   0.0840
  -2.250   0.2385   0.01162   0.00395  -0.1030   0.8558   0.0914
  -2.000   0.2669   0.01147   0.00378  -0.1029   0.8353   0.1000
  -1.750   0.2959   0.01136   0.00362  -0.1028   0.8084   0.1075
  -1.500   0.3260   0.01124   0.00334  -0.1029   0.7763   0.1135
  -1.250   0.3550   0.01122   0.00315  -0.1028   0.7466   0.1201
  -1.000   0.3823   0.01127   0.00303  -0.1023   0.7222   0.1294
  -0.750   0.4088   0.01134   0.00294  -0.1018   0.7014   0.1382
  -0.500   0.4349   0.01136   0.00287  -0.1013   0.6833   0.1454
  -0.250   0.4610   0.01142   0.00280  -0.1007   0.6669   0.1537
   0.000   0.4868   0.01144   0.00277  -0.1002   0.6513   0.1611
   0.250   0.5126   0.01151   0.00273  -0.0996   0.6358   0.1685
   0.500   0.5379   0.01155   0.00273  -0.0990   0.6189   0.1754
   0.750   0.5631   0.01162   0.00272  -0.0983   0.6002   0.1829
   1.000   0.5883   0.01168   0.00275  -0.0977   0.5832   0.1897
   1.250   0.6138   0.01176   0.00278  -0.0971   0.5696   0.1977
   1.500   0.6394   0.01182   0.00286  -0.0966   0.5587   0.2090
   1.750   0.6651   0.01189   0.00295  -0.0961   0.5477   0.2246
   2.250   0.7164   0.01201   0.00316  -0.0951   0.5262   0.2675
   2.750   0.7774   0.01089   0.00341  -0.0963   0.5011   1.0000
   3.000   0.8023   0.01108   0.00353  -0.0956   0.4871   1.0000
   3.250   0.8272   0.01127   0.00366  -0.0949   0.4731   1.0000
   3.500   0.8521   0.01146   0.00381  -0.0943   0.4596   1.0000
   3.750   0.8771   0.01166   0.00398  -0.0936   0.4472   1.0000
   4.000   0.9018   0.01187   0.00417  -0.0930   0.4336   1.0000
   4.250   0.9264   0.01209   0.00437  -0.0923   0.4193   1.0000
   4.500   0.9511   0.01231   0.00459  -0.0916   0.4068   1.0000
   4.750   0.9755   0.01255   0.00484  -0.0909   0.3930   1.0000
   5.000   0.9995   0.01281   0.00510  -0.0901   0.3769   1.0000
   5.250   1.0228   0.01312   0.00536  -0.0893   0.3567   1.0000
   5.500   1.0433   0.01359   0.00565  -0.0880   0.3150   1.0000
   6.000   1.0824   0.01487   0.00651  -0.0853   0.2336   1.0000
   6.250   1.1018   0.01558   0.00703  -0.0841   0.1961   1.0000
   6.500   1.1186   0.01655   0.00767  -0.0825   0.1341   1.0000
   6.750   1.1330   0.01779   0.00857  -0.0806   0.0891   1.0000
   7.000   1.1452   0.01924   0.00968  -0.0784   0.0276   1.0000
   7.250   1.1636   0.02005   0.01056  -0.0768   0.0215   1.0000
   7.500   1.1818   0.02082   0.01147  -0.0752   0.0188   1.0000
   7.750   1.1983   0.02174   0.01252  -0.0733   0.0162   1.0000
   8.000   1.2126   0.02282   0.01380  -0.0712   0.0145   1.0000
   8.250   1.2248   0.02401   0.01518  -0.0688   0.0137   1.0000
   8.500   1.2378   0.02502   0.01634  -0.0666   0.0133   1.0000
   8.750   1.2487   0.02605   0.01750  -0.0641   0.0127   1.0000
   9.000   1.2564   0.02717   0.01879  -0.0612   0.0121   1.0000
   9.250   1.2637   0.02832   0.02004  -0.0584   0.0111   1.0000
   9.500   1.2682   0.02968   0.02151  -0.0554   0.0107   1.0000
   9.750   1.2711   0.03123   0.02317  -0.0525   0.0103   1.0000
  10.000   1.2735   0.03291   0.02494  -0.0498   0.0101   1.0000
  10.250   1.2749   0.03480   0.02691  -0.0473   0.0098   1.0000
  10.500   1.2765   0.03683   0.02903  -0.0452   0.0095   1.0000
  10.750   1.2788   0.03898   0.03126  -0.0432   0.0094   1.0000
  11.000   1.2812   0.04140   0.03373  -0.0415   0.0091   1.0000
  11.250   1.2870   0.04389   0.03629  -0.0400   0.0090   1.0000
  11.500   1.2960   0.04664   0.03912  -0.0385   0.0087   1.0000
  11.750   1.2986   0.04870   0.04138  -0.0374   0.0084   1.0000
  12.000   1.3012   0.05101   0.04389  -0.0365   0.0081   1.0000
  12.250   1.3033   0.05362   0.04669  -0.0358   0.0078   1.0000
  12.500   1.3040   0.05648   0.04980  -0.0353   0.0075   1.0000
  12.750   1.3038   0.05970   0.05321  -0.0350   0.0074   1.0000
  13.000   1.3016   0.06318   0.05689  -0.0349   0.0073   1.0000
  13.250   1.2976   0.06701   0.06093  -0.0352   0.0072   1.0000
  13.500   1.2920   0.07114   0.06526  -0.0358   0.0072   1.0000
  13.750   1.2846   0.07562   0.06995  -0.0368   0.0071   1.0000
  14.000   1.2755   0.08049   0.07503  -0.0382   0.0070   1.0000
  14.250   1.2654   0.08567   0.08041  -0.0401   0.0070   1.0000
  14.500   1.2539   0.09132   0.08627  -0.0425   0.0070   1.0000
  14.750   1.2418   0.09732   0.09246  -0.0453   0.0070   1.0000
  15.000   1.2288   0.10371   0.09905  -0.0485   0.0070   1.0000
  15.250   1.2153   0.11056   0.10610  -0.0522   0.0070   1.0000
  15.500   1.2016   0.11777   0.11349  -0.0564   0.0071   1.0000
  15.750   1.1878   0.12535   0.12125  -0.0610   0.0071   1.0000
  16.000   1.1734   0.13350   0.12956  -0.0660   0.0071   1.0000
  16.250   1.1593   0.14204   0.13826  -0.0715   0.0072   1.0000
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