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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 500,000
Max Cl/Cd: 73.86 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe235-il-500000.txt
Download as CSV file: xf-goe235-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4450   0.09514   0.09283   0.0014   1.0000   0.0245
  -7.750  -0.4380   0.09210   0.08981  -0.0004   1.0000   0.0249
  -7.500  -0.4310   0.08901   0.08674  -0.0025   1.0000   0.0253
  -7.250  -0.4215   0.08565   0.08339  -0.0058   1.0000   0.0259
  -7.000  -0.4076   0.08180   0.07954  -0.0109   1.0000   0.0267
  -6.750  -0.3796   0.07563   0.07330  -0.0268   1.0000   0.0273
  -6.500  -0.3610   0.07057   0.06820  -0.0323   1.0000   0.0274
  -6.250  -0.3497   0.06745   0.06510  -0.0319   1.0000   0.0276
  -6.000  -0.3353   0.06462   0.06229  -0.0326   1.0000   0.0277
  -5.750  -0.3196   0.06183   0.05950  -0.0339   1.0000   0.0280
  -5.500  -0.3003   0.05889   0.05655  -0.0363   0.9981   0.0283
  -5.250  -0.2656   0.05509   0.05268  -0.0423   0.9899   0.0290
  -5.000  -0.2290   0.05117   0.04867  -0.0484   0.9793   0.0300
  -4.750  -0.1717   0.04506   0.04210  -0.0586   0.9653   0.0319
  -4.500  -0.1522   0.04117   0.03816  -0.0598   0.9469   0.0322
  -4.250  -0.1340   0.03905   0.03599  -0.0595   0.9268   0.0324
  -4.000  -0.1138   0.03709   0.03395  -0.0594   0.9061   0.0327
  -3.750  -0.0912   0.03513   0.03186  -0.0595   0.8877   0.0333
  -3.500  -0.0664   0.03307   0.02964  -0.0599   0.8717   0.0341
  -3.250  -0.0390   0.03085   0.02719  -0.0604   0.8572   0.0356
  -3.000  -0.0033   0.02752   0.02320  -0.0611   0.8454   0.0375
  -2.750   0.0206   0.02546   0.02112  -0.0615   0.8332   0.0379
  -2.500   0.0460   0.02411   0.01969  -0.0617   0.8217   0.0385
  -2.250   0.0725   0.02286   0.01832  -0.0618   0.8105   0.0395
  -2.000   0.1004   0.02156   0.01681  -0.0618   0.7982   0.0410
  -1.750   0.1328   0.02019   0.01487  -0.0614   0.7854   0.0440
  -1.500   0.1593   0.01847   0.01315  -0.0618   0.7719   0.0448
  -1.250   0.1866   0.01745   0.01206  -0.0618   0.7571   0.0459
  -1.000   0.2148   0.01661   0.01109  -0.0618   0.7410   0.0480
  -0.750   0.2451   0.01752   0.01161  -0.0610   0.7239   0.0511
  -0.500   0.2723   0.01481   0.00885  -0.0615   0.7065   0.0533
   0.000   0.3287   0.01378   0.00743  -0.0612   0.6665   0.0618
   0.250   0.3563   0.01307   0.00666  -0.0611   0.6462   0.0643
   0.500   0.3843   0.01308   0.00648  -0.0608   0.6226   0.0694
   0.750   0.4143   0.01159   0.00467  -0.0601   0.6027   0.0482
   1.000   0.4427   0.01097   0.00387  -0.0597   0.5772   0.0452
   1.250   0.4703   0.01074   0.00354  -0.0595   0.5326   0.0462
   1.500   0.4961   0.01107   0.00335  -0.0593   0.4133   0.0475
   1.750   0.5224   0.01134   0.00323  -0.0591   0.3213   0.0478
   2.000   0.5487   0.01166   0.00319  -0.0590   0.2451   0.0487
   2.250   0.5762   0.01173   0.00316  -0.0589   0.2247   0.0500
   2.500   0.6039   0.01179   0.00316  -0.0588   0.2127   0.0513
   2.750   0.6316   0.01172   0.00307  -0.0588   0.2030   0.0551
   3.000   0.6595   0.01173   0.00308  -0.0588   0.1948   0.0587
   3.250   0.6872   0.01178   0.00309  -0.0587   0.1853   0.0635
   3.500   0.7149   0.01186   0.00313  -0.0586   0.1734   0.0741
   3.750   0.7380   0.01009   0.00332  -0.0579   0.1623   1.0000
   4.000   0.7652   0.01036   0.00342  -0.0578   0.1411   1.0000
   4.250   0.7892   0.01137   0.00393  -0.0574   0.0494   1.0000
   4.500   0.8160   0.01172   0.00423  -0.0571   0.0452   1.0000
   4.750   0.8427   0.01208   0.00459  -0.0569   0.0424   1.0000
   5.000   0.8694   0.01242   0.00494  -0.0566   0.0410   1.0000
   5.250   0.8958   0.01280   0.00533  -0.0563   0.0400   1.0000
   5.500   0.9220   0.01321   0.00576  -0.0560   0.0390   1.0000
   5.750   0.9478   0.01367   0.00624  -0.0556   0.0382   1.0000
   6.000   0.9733   0.01418   0.00678  -0.0552   0.0374   1.0000
   6.250   0.9982   0.01476   0.00738  -0.0548   0.0368   1.0000
   6.500   1.0224   0.01545   0.00809  -0.0542   0.0361   1.0000
   6.750   1.0448   0.01642   0.00910  -0.0535   0.0352   1.0000
   7.000   1.0676   0.01728   0.01000  -0.0528   0.0346   1.0000
   7.250   1.0915   0.01792   0.01067  -0.0522   0.0343   1.0000
   7.500   1.1149   0.01863   0.01143  -0.0515   0.0340   1.0000
   7.750   1.1378   0.01942   0.01225  -0.0508   0.0336   1.0000
   8.000   1.1604   0.02026   0.01313  -0.0501   0.0333   1.0000
   8.250   1.1829   0.02111   0.01403  -0.0493   0.0327   1.0000
   8.500   1.2051   0.02198   0.01493  -0.0486   0.0321   1.0000
   8.750   1.2271   0.02294   0.01593  -0.0478   0.0315   1.0000
   9.000   1.2488   0.02399   0.01701  -0.0470   0.0311   1.0000
   9.250   1.2704   0.02511   0.01816  -0.0463   0.0307   1.0000
   9.500   1.2917   0.02635   0.01944  -0.0455   0.0302   1.0000
   9.750   1.3129   0.02785   0.02096  -0.0448   0.0297   1.0000
  10.000   1.3345   0.03077   0.02387  -0.0445   0.0290   1.0000
  10.250   1.3525   0.03234   0.02565  -0.0434   0.0285   1.0000
  10.500   1.3705   0.03335   0.02684  -0.0422   0.0282   1.0000
  10.750   1.3876   0.03473   0.02841  -0.0410   0.0279   1.0000
  11.000   1.4034   0.03637   0.03024  -0.0397   0.0275   1.0000
  11.250   1.4175   0.03812   0.03219  -0.0383   0.0271   1.0000
  11.500   1.4296   0.03985   0.03410  -0.0367   0.0266   1.0000
  11.750   1.4401   0.04159   0.03601  -0.0351   0.0260   1.0000
  12.000   1.4492   0.04343   0.03801  -0.0335   0.0256   1.0000
  12.250   1.4567   0.04538   0.04008  -0.0318   0.0252   1.0000
  12.500   1.4664   0.04719   0.04194  -0.0304   0.0248   1.0000
  12.750   1.4792   0.04929   0.04404  -0.0296   0.0244   1.0000
  13.000   1.4802   0.05244   0.04732  -0.0277   0.0241   1.0000
  13.250   1.4717   0.05615   0.05122  -0.0252   0.0240   1.0000
  13.500   1.4575   0.05977   0.05505  -0.0227   0.0239   1.0000
  13.750   1.4400   0.06372   0.05921  -0.0209   0.0239   1.0000
  14.000   1.4210   0.06792   0.06361  -0.0201   0.0238   1.0000
  14.250   1.4003   0.07258   0.06846  -0.0201   0.0238   1.0000
  14.500   1.3798   0.07745   0.07352  -0.0211   0.0238   1.0000
  14.750   1.3591   0.08270   0.07894  -0.0231   0.0238   1.0000
  15.000   1.3381   0.08842   0.08484  -0.0260   0.0239   1.0000
  15.250   1.3172   0.09454   0.09112  -0.0297   0.0239   1.0000
  15.500   1.2939   0.10167   0.09843  -0.0348   0.0240   1.0000
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