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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 200,000
Max Cl/Cd: 75.44 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe335-il-200000-n5.txt
Download as CSV file: xf-goe335-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 335 (D.F.W.) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3052   0.08950   0.08631  -0.0235   1.0000   0.0214
  -7.000  -0.3109   0.08765   0.08453  -0.0220   1.0000   0.0213
  -6.750  -0.3143   0.08546   0.08242  -0.0215   1.0000   0.0217
  -6.500  -0.2883   0.07856   0.07550  -0.0328   0.9923   0.0153
  -6.250  -0.2636   0.07378   0.07070  -0.0388   0.9860   0.0149
  -6.000  -0.2331   0.06850   0.06538  -0.0474   0.9776   0.0150
  -5.250  -0.1293   0.05192   0.04849  -0.0717   0.9431   0.0159
  -4.750  -0.0616   0.04085   0.03706  -0.0837   0.9145   0.0166
  -4.500  -0.0307   0.03968   0.03579  -0.0862   0.9000   0.0185
  -4.250   0.0069   0.03580   0.03166  -0.0906   0.8859   0.0205
  -4.000   0.0452   0.03045   0.02588  -0.0948   0.8722   0.0217
  -3.750   0.0822   0.02472   0.01946  -0.0972   0.8589   0.0250
  -3.500   0.1121   0.02117   0.01534  -0.0985   0.8454   0.0273
  -3.250   0.1408   0.02029   0.01423  -0.0990   0.8314   0.0299
  -3.000   0.1690   0.01886   0.01238  -0.0990   0.8177   0.0336
  -2.750   0.1969   0.01728   0.01030  -0.0987   0.8052   0.0357
  -2.500   0.2245   0.01664   0.00929  -0.0984   0.7940   0.0383
  -2.250   0.2510   0.01516   0.00747  -0.0981   0.7838   0.0398
  -2.000   0.2775   0.01442   0.00654  -0.0977   0.7729   0.0411
  -1.750   0.3040   0.01385   0.00583  -0.0973   0.7620   0.0422
  -1.500   0.3305   0.01351   0.00538  -0.0969   0.7514   0.0448
  -1.250   0.3569   0.01309   0.00483  -0.0964   0.7407   0.0459
  -1.000   0.3830   0.01265   0.00429  -0.0959   0.7286   0.0458
  -0.750   0.4089   0.01229   0.00385  -0.0953   0.7157   0.0460
  -0.500   0.4348   0.01201   0.00349  -0.0948   0.7018   0.0463
  -0.250   0.4606   0.01179   0.00318  -0.0942   0.6870   0.0469
   0.000   0.4864   0.01163   0.00293  -0.0936   0.6715   0.0480
   0.250   0.5122   0.01153   0.00271  -0.0930   0.6547   0.0497
   0.500   0.5379   0.01145   0.00254  -0.0924   0.6353   0.0529
   1.000   0.5877   0.01124   0.00240  -0.0911   0.5878   0.1394
   1.250   0.6103   0.01082   0.00248  -0.0903   0.5596   0.3724
   1.500   0.6448   0.00977   0.00249  -0.0916   0.5260   1.0000
   1.750   0.6686   0.01003   0.00252  -0.0907   0.4971   1.0000
   2.000   0.6927   0.01030   0.00261  -0.0899   0.4738   1.0000
   2.250   0.7169   0.01058   0.00272  -0.0892   0.4558   1.0000
   2.500   0.7414   0.01084   0.00285  -0.0885   0.4413   1.0000
   2.750   0.7662   0.01110   0.00301  -0.0879   0.4291   1.0000
   3.000   0.7911   0.01136   0.00320  -0.0874   0.4191   1.0000
   3.250   0.8159   0.01163   0.00339  -0.0868   0.4101   1.0000
   3.500   0.8413   0.01187   0.00360  -0.0864   0.4017   1.0000
   3.750   0.8661   0.01215   0.00384  -0.0858   0.3943   1.0000
   4.000   0.8915   0.01238   0.00407  -0.0854   0.3863   1.0000
   4.250   0.9163   0.01266   0.00432  -0.0849   0.3792   1.0000
   4.500   0.9417   0.01289   0.00460  -0.0845   0.3719   1.0000
   4.750   0.9664   0.01317   0.00488  -0.0839   0.3644   1.0000
   5.000   0.9914   0.01340   0.00516  -0.0834   0.3558   1.0000
   5.250   1.0161   0.01368   0.00546  -0.0829   0.3489   1.0000
   5.500   1.0412   0.01392   0.00580  -0.0825   0.3420   1.0000
   5.750   1.0654   0.01419   0.00611  -0.0819   0.3325   1.0000
   6.000   1.0881   0.01445   0.00634  -0.0810   0.3097   1.0000
   6.250   1.1112   0.01473   0.00663  -0.0803   0.2888   1.0000
   6.500   1.1337   0.01508   0.00698  -0.0795   0.2587   1.0000
   6.750   1.1515   0.01587   0.00743  -0.0781   0.1908   1.0000
   7.000   1.1582   0.01804   0.00880  -0.0755   0.0772   1.0000
   7.250   1.1700   0.01962   0.01008  -0.0733   0.0228   1.0000
   7.500   1.1880   0.02051   0.01105  -0.0717   0.0180   1.0000
   7.750   1.2046   0.02151   0.01225  -0.0700   0.0148   1.0000
   8.000   1.2203   0.02253   0.01347  -0.0681   0.0137   1.0000
   8.250   1.2350   0.02353   0.01471  -0.0662   0.0131   1.0000
   8.500   1.2479   0.02462   0.01596  -0.0641   0.0121   1.0000
   8.750   1.2585   0.02578   0.01726  -0.0618   0.0110   1.0000
   9.000   1.2653   0.02702   0.01862  -0.0590   0.0103   1.0000
   9.250   1.2685   0.02844   0.02017  -0.0557   0.0099   1.0000
   9.500   1.2696   0.03007   0.02191  -0.0525   0.0096   1.0000
   9.750   1.2692   0.03194   0.02388  -0.0495   0.0093   1.0000
  10.000   1.2686   0.03401   0.02606  -0.0469   0.0091   1.0000
  10.250   1.2666   0.03652   0.02866  -0.0444   0.0088   1.0000
  10.500   1.2681   0.03916   0.03140  -0.0423   0.0086   1.0000
  10.750   1.2750   0.04121   0.03358  -0.0408   0.0084   1.0000
  11.000   1.2817   0.04319   0.03572  -0.0395   0.0082   1.0000
  11.250   1.2877   0.04525   0.03802  -0.0384   0.0078   1.0000
  11.500   1.2923   0.04749   0.04042  -0.0374   0.0073   1.0000
  11.750   1.2960   0.05001   0.04311  -0.0365   0.0070   1.0000
  12.000   1.2986   0.05282   0.04611  -0.0357   0.0069   1.0000
  12.250   1.2997   0.05589   0.04937  -0.0350   0.0068   1.0000
  12.500   1.2989   0.05919   0.05288  -0.0346   0.0066   1.0000
  12.750   1.2961   0.06277   0.05665  -0.0345   0.0065   1.0000
  13.000   1.2914   0.06671   0.06081  -0.0347   0.0065   1.0000
  13.250   1.2847   0.07100   0.06531  -0.0353   0.0064   1.0000
  13.500   1.2763   0.07567   0.07019  -0.0364   0.0064   1.0000
  13.750   1.2667   0.08066   0.07539  -0.0379   0.0063   1.0000
  14.000   1.2551   0.08618   0.08113  -0.0400   0.0064   1.0000
  14.250   1.2427   0.09214   0.08731  -0.0426   0.0064   1.0000
  14.500   1.2296   0.09852   0.09390  -0.0457   0.0064   1.0000
  14.750   1.2155   0.10543   0.10102  -0.0494   0.0064   1.0000
  15.000   1.2011   0.11280   0.10859  -0.0536   0.0064   1.0000
  15.250   1.1861   0.12063   0.11661  -0.0582   0.0065   1.0000
  15.500   1.1708   0.12888   0.12503  -0.0633   0.0065   1.0000
  15.750   1.1554   0.13761   0.13393  -0.0687   0.0066   1.0000
  16.000   1.1400   0.14687   0.14334  -0.0746   0.0067   1.0000
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