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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 200,000
Max Cl/Cd: 57.61 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe235-il-200000-n5.txt
Download as CSV file: xf-goe235-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 235 (SCHTTE-LANZ) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4390   0.10004   0.09632  -0.0003   1.0000   0.0331
  -8.000  -0.4348   0.09690   0.09321  -0.0038   1.0000   0.0335
  -7.750  -0.4310   0.09366   0.09000  -0.0088   1.0000   0.0337
  -7.500  -0.4188   0.08938   0.08571  -0.0181   1.0000   0.0338
  -7.250  -0.4099   0.08599   0.08237  -0.0153   1.0000   0.0341
  -7.000  -0.3989   0.08286   0.07926  -0.0153   1.0000   0.0344
  -6.750  -0.3862   0.07964   0.07606  -0.0174   1.0000   0.0348
  -6.500  -0.3722   0.07637   0.07280  -0.0202   1.0000   0.0352
  -6.250  -0.3567   0.07304   0.06947  -0.0234   1.0000   0.0358
  -6.000  -0.3399   0.06966   0.06608  -0.0269   1.0000   0.0366
  -5.750  -0.3218   0.06623   0.06263  -0.0306   1.0000   0.0375
  -5.500  -0.2950   0.06210   0.05838  -0.0377   0.9986   0.0390
  -5.250  -0.2522   0.05653   0.05255  -0.0475   0.9856   0.0395
  -5.000  -0.2297   0.05337   0.04944  -0.0491   0.9755   0.0399
  -4.750  -0.2022   0.05034   0.04637  -0.0519   0.9647   0.0405
  -4.500  -0.1726   0.04735   0.04328  -0.0551   0.9534   0.0413
  -4.250  -0.1419   0.04436   0.04017  -0.0582   0.9417   0.0424
  -4.000  -0.1091   0.04130   0.03691  -0.0613   0.9292   0.0443
  -3.750  -0.0679   0.03808   0.03305  -0.0646   0.9146   0.0457
  -3.500  -0.0464   0.03506   0.03004  -0.0651   0.8972   0.0462
  -3.250  -0.0254   0.03327   0.02824  -0.0649   0.8771   0.0472
  -3.000  -0.0017   0.03162   0.02643  -0.0646   0.8577   0.0487
  -2.750   0.0246   0.02977   0.02433  -0.0645   0.8402   0.0502
  -2.250   0.0852   0.02419   0.01781  -0.0645   0.8142   0.0387
  -2.000   0.1121   0.02267   0.01608  -0.0644   0.8025   0.0381
  -1.750   0.1401   0.02121   0.01438  -0.0644   0.7895   0.0377
  -1.500   0.1685   0.01994   0.01281  -0.0641   0.7745   0.0382
  -1.250   0.1972   0.01889   0.01139  -0.0637   0.7584   0.0390
  -1.000   0.2251   0.01785   0.01016  -0.0634   0.7417   0.0388
  -0.750   0.2529   0.01694   0.00904  -0.0631   0.7231   0.0388
  -0.500   0.2808   0.01616   0.00805  -0.0627   0.7030   0.0389
  -0.250   0.3085   0.01551   0.00720  -0.0623   0.6844   0.0391
   0.250   0.3632   0.01441   0.00581  -0.0615   0.6473   0.0401
   0.500   0.3903   0.01411   0.00546  -0.0612   0.6297   0.0416
   0.750   0.4175   0.01387   0.00510  -0.0608   0.6102   0.0433
   1.000   0.4449   0.01357   0.00472  -0.0604   0.5889   0.0440
   1.250   0.4722   0.01333   0.00439  -0.0601   0.5578   0.0448
   1.500   0.4983   0.01330   0.00408  -0.0595   0.4815   0.0456
   1.750   0.5225   0.01358   0.00391  -0.0591   0.3856   0.0468
   2.000   0.5475   0.01398   0.00393  -0.0588   0.2937   0.0488
   2.250   0.5736   0.01428   0.00399  -0.0587   0.2504   0.0520
   2.500   0.6004   0.01438   0.00400  -0.0585   0.2326   0.0542
   2.750   0.6273   0.01452   0.00405  -0.0584   0.2179   0.0571
   3.000   0.6543   0.01466   0.00412  -0.0582   0.2060   0.0610
   3.250   0.6813   0.01476   0.00422  -0.0580   0.1976   0.0699
   3.500   0.7084   0.01462   0.00441  -0.0580   0.1907   0.2121
   3.750   0.7313   0.01328   0.00458  -0.0569   0.1831   1.0000
   4.000   0.7584   0.01351   0.00475  -0.0567   0.1744   1.0000
   4.250   0.7851   0.01380   0.00496  -0.0564   0.1660   1.0000
   4.500   0.8117   0.01409   0.00516  -0.0562   0.1516   1.0000
   4.750   0.8358   0.01485   0.00547  -0.0558   0.0725   1.0000
   5.000   0.8598   0.01569   0.00613  -0.0553   0.0490   1.0000
   5.250   0.8854   0.01617   0.00658  -0.0549   0.0457   1.0000
   5.500   0.9108   0.01667   0.00708  -0.0545   0.0437   1.0000
   5.750   0.9360   0.01721   0.00765  -0.0541   0.0422   1.0000
   6.000   0.9612   0.01771   0.00820  -0.0536   0.0413   1.0000
   6.250   0.9862   0.01823   0.00878  -0.0532   0.0405   1.0000
   6.500   1.0107   0.01879   0.00942  -0.0527   0.0397   1.0000
   6.750   1.0348   0.01940   0.01009  -0.0522   0.0387   1.0000
   7.000   1.0581   0.02007   0.01081  -0.0516   0.0377   1.0000
   7.250   1.0806   0.02083   0.01161  -0.0509   0.0368   1.0000
   7.500   1.1020   0.02171   0.01252  -0.0502   0.0362   1.0000
   7.750   1.1221   0.02273   0.01355  -0.0493   0.0356   1.0000
   8.000   1.1417   0.02382   0.01465  -0.0483   0.0351   1.0000
   8.250   1.1627   0.02471   0.01559  -0.0474   0.0348   1.0000
   8.500   1.1833   0.02564   0.01660  -0.0465   0.0344   1.0000
   8.750   1.2036   0.02660   0.01764  -0.0456   0.0339   1.0000
   9.000   1.2236   0.02761   0.01871  -0.0447   0.0332   1.0000
   9.250   1.2431   0.02868   0.01986  -0.0437   0.0325   1.0000
   9.500   1.2622   0.02984   0.02107  -0.0427   0.0320   1.0000
   9.750   1.2811   0.03106   0.02236  -0.0417   0.0315   1.0000
  10.000   1.2996   0.03235   0.02372  -0.0407   0.0311   1.0000
  10.250   1.3177   0.03372   0.02516  -0.0397   0.0306   1.0000
  10.500   1.3355   0.03524   0.02671  -0.0388   0.0301   1.0000
  10.750   1.3543   0.03734   0.02881  -0.0382   0.0294   1.0000
  11.000   1.3681   0.03873   0.03041  -0.0368   0.0290   1.0000
  11.250   1.3806   0.04024   0.03215  -0.0353   0.0285   1.0000
  11.500   1.3917   0.04195   0.03410  -0.0337   0.0282   1.0000
  11.750   1.4004   0.04380   0.03617  -0.0320   0.0278   1.0000
  12.000   1.4052   0.04567   0.03827  -0.0299   0.0273   1.0000
  12.250   1.4067   0.04763   0.04042  -0.0277   0.0269   1.0000
  12.500   1.4069   0.04972   0.04269  -0.0257   0.0265   1.0000
  12.750   1.4064   0.05196   0.04510  -0.0242   0.0261   1.0000
  13.000   1.4056   0.05435   0.04766  -0.0230   0.0257   1.0000
  13.250   1.4048   0.05690   0.05033  -0.0221   0.0254   1.0000
  13.500   1.4007   0.05985   0.05344  -0.0215   0.0252   1.0000
  13.750   1.3953   0.06311   0.05686  -0.0213   0.0250   1.0000
  14.000   1.3886   0.06671   0.06061  -0.0214   0.0248   1.0000
  14.250   1.3802   0.07068   0.06474  -0.0220   0.0246   1.0000
  14.500   1.3698   0.07514   0.06936  -0.0230   0.0245   1.0000
  14.750   1.3570   0.08014   0.07453  -0.0245   0.0243   1.0000
  15.000   1.3385   0.08607   0.08067  -0.0272   0.0243   1.0000
  15.250   1.3171   0.09279   0.08761  -0.0309   0.0242   1.0000
  15.500   1.2946   0.10027   0.09531  -0.0354   0.0242   1.0000
  15.750   1.2716   0.10856   0.10382  -0.0408   0.0242   1.0000
  16.000   1.2478   0.11779   0.11324  -0.0471   0.0242   1.0000
  16.250   1.2228   0.12809   0.12372  -0.0543   0.0243   1.0000
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