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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 200,000
Max Cl/Cd: 77.8 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe180-il-200000-n5.txt
Download as CSV file: xf-goe180-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) 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  -0.3531   0.08932   0.08590  -0.0295   1.0000   0.0226
  -7.750  -0.3554   0.08692   0.08356  -0.0283   1.0000   0.0224
  -7.500  -0.3596   0.08434   0.08105  -0.0276   1.0000   0.0222
  -7.250  -0.3631   0.08151   0.07828  -0.0278   1.0000   0.0220
  -6.750  -0.3218   0.06754   0.06424  -0.0482   0.9881   0.0233
  -6.500  -0.2997   0.06737   0.06408  -0.0480   0.9841   0.0252
  -6.250  -0.2710   0.06167   0.05830  -0.0565   0.9768   0.0259
  -6.000  -0.2418   0.05513   0.05163  -0.0650   0.9677   0.0258
  -5.750  -0.2104   0.04882   0.04513  -0.0726   0.9592   0.0266
  -5.500  -0.1714   0.03985   0.03572  -0.0818   0.9527   0.0286
  -5.250  -0.1381   0.03060   0.02562  -0.0875   0.9442   0.0297
  -5.000  -0.1064   0.02801   0.02285  -0.0903   0.9388   0.0313
  -4.750  -0.0759   0.02595   0.02055  -0.0919   0.9307   0.0324
  -4.500  -0.0405   0.02280   0.01688  -0.0944   0.9246   0.0333
  -4.250  -0.0078   0.02085   0.01454  -0.0957   0.9159   0.0349
  -4.000   0.0278   0.01903   0.01228  -0.0974   0.9083   0.0361
  -3.750   0.0599   0.01762   0.01051  -0.0983   0.8980   0.0367
  -3.500   0.0919   0.01653   0.00914  -0.0990   0.8873   0.0372
  -3.250   0.1232   0.01572   0.00810  -0.0995   0.8752   0.0379
  -3.000   0.1527   0.01484   0.00704  -0.0997   0.8610   0.0391
  -2.750   0.1811   0.01410   0.00620  -0.0996   0.8447   0.0399
  -2.500   0.2089   0.01354   0.00554  -0.0994   0.8263   0.0405
  -2.250   0.2366   0.01308   0.00499  -0.0991   0.8059   0.0412
  -2.000   0.2639   0.01271   0.00452  -0.0988   0.7826   0.0421
  -1.750   0.2910   0.01243   0.00410  -0.0983   0.7571   0.0431
  -1.500   0.3177   0.01223   0.00375  -0.0978   0.7294   0.0442
  -1.250   0.3441   0.01211   0.00345  -0.0973   0.7005   0.0456
  -1.000   0.3703   0.01206   0.00321  -0.0967   0.6722   0.0480
  -0.750   0.3965   0.01201   0.00304  -0.0962   0.6470   0.0517
  -0.500   0.4228   0.01200   0.00291  -0.0958   0.6252   0.0561
  -0.250   0.4492   0.01199   0.00282  -0.0953   0.6065   0.0692
   0.000   0.4757   0.01195   0.00277  -0.0950   0.5901   0.1004
   0.250   0.5021   0.01183   0.00278  -0.0948   0.5758   0.1672
   0.500   0.5286   0.01171   0.00282  -0.0946   0.5629   0.2514
   0.750   0.5519   0.01087   0.00294  -0.0941   0.5516   0.5975
   1.250   0.6063   0.01037   0.00298  -0.0930   0.5330   1.0000
   1.500   0.6334   0.01053   0.00304  -0.0928   0.5248   1.0000
   1.750   0.6601   0.01072   0.00311  -0.0925   0.5162   1.0000
   2.000   0.6871   0.01088   0.00320  -0.0923   0.5068   1.0000
   2.250   0.7137   0.01107   0.00329  -0.0920   0.4971   1.0000
   2.500   0.7402   0.01125   0.00339  -0.0917   0.4865   1.0000
   2.750   0.7669   0.01141   0.00351  -0.0914   0.4770   1.0000
   3.000   0.7935   0.01161   0.00364  -0.0911   0.4697   1.0000
   3.250   0.8205   0.01177   0.00380  -0.0910   0.4626   1.0000
   3.500   0.8469   0.01197   0.00396  -0.0907   0.4550   1.0000
   3.750   0.8736   0.01213   0.00414  -0.0904   0.4463   1.0000
   4.000   0.8997   0.01234   0.00431  -0.0901   0.4374   1.0000
   4.250   0.9260   0.01252   0.00451  -0.0898   0.4272   1.0000
   4.500   0.9521   0.01271   0.00470  -0.0895   0.4165   1.0000
   4.750   0.9778   0.01293   0.00491  -0.0891   0.4047   1.0000
   5.000   1.0033   0.01315   0.00514  -0.0886   0.3919   1.0000
   5.250   1.0288   0.01337   0.00537  -0.0882   0.3780   1.0000
   5.500   1.0541   0.01361   0.00562  -0.0878   0.3626   1.0000
   5.750   1.0791   0.01387   0.00590  -0.0873   0.3440   1.0000
   6.000   1.1031   0.01419   0.00619  -0.0867   0.3215   1.0000
   6.250   1.1264   0.01459   0.00653  -0.0860   0.2975   1.0000
   7.000   1.1942   0.01604   0.00788  -0.0837   0.2500   1.0000
   7.250   1.2167   0.01653   0.00839  -0.0829   0.2394   1.0000
   7.500   1.2383   0.01710   0.00895  -0.0820   0.2275   1.0000
   7.750   1.2592   0.01770   0.00956  -0.0810   0.2118   1.0000
   8.000   1.2801   0.01828   0.01012  -0.0801   0.1930   1.0000
   8.250   1.3007   0.01887   0.01068  -0.0791   0.1729   1.0000
   8.500   1.3208   0.01948   0.01126  -0.0781   0.1509   1.0000
   8.750   1.3380   0.02033   0.01200  -0.0768   0.1291   1.0000
   9.000   1.3548   0.02120   0.01283  -0.0753   0.1118   1.0000
   9.250   1.3700   0.02218   0.01375  -0.0737   0.0828   1.0000
  10.000   1.3893   0.02676   0.01803  -0.0652   0.0247   1.0000
  10.250   1.3956   0.02807   0.01942  -0.0624   0.0219   1.0000
  10.500   1.4026   0.02935   0.02085  -0.0599   0.0201   1.0000
  10.750   1.4093   0.03068   0.02233  -0.0576   0.0186   1.0000
  11.000   1.4138   0.03223   0.02402  -0.0553   0.0175   1.0000
  11.250   1.4157   0.03407   0.02599  -0.0531   0.0167   1.0000
  11.500   1.4140   0.03633   0.02840  -0.0510   0.0160   1.0000
  11.750   1.4084   0.03912   0.03132  -0.0492   0.0154   1.0000
  12.000   1.4087   0.04156   0.03393  -0.0481   0.0150   1.0000
  12.250   1.4075   0.04430   0.03683  -0.0473   0.0145   1.0000
  12.500   1.4054   0.04733   0.04001  -0.0468   0.0140   1.0000
  12.750   1.4024   0.05061   0.04345  -0.0467   0.0135   1.0000
  13.000   1.3986   0.05416   0.04714  -0.0469   0.0131   1.0000
  13.250   1.3938   0.05795   0.05107  -0.0473   0.0127   1.0000
  13.500   1.3881   0.06195   0.05519  -0.0479   0.0124   1.0000
  13.750   1.3816   0.06611   0.05948  -0.0486   0.0122   1.0000
  14.000   1.3747   0.07040   0.06387  -0.0494   0.0120   1.0000
  14.250   1.3673   0.07476   0.06835  -0.0502   0.0118   1.0000
  14.500   1.3600   0.07916   0.07285  -0.0510   0.0116   1.0000
  14.750   1.3527   0.08357   0.07736  -0.0518   0.0114   1.0000
  15.000   1.3458   0.08780   0.08167  -0.0523   0.0112   1.0000
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