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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 100,000
Max Cl/Cd: 48.01 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe235-il-100000-n5.txt
Download as CSV file: xf-goe235-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4252   0.09986   0.09465  -0.0035   1.0000   0.0507
  -7.750  -0.4204   0.09699   0.09183  -0.0062   1.0000   0.0517
  -7.500  -0.4152   0.09416   0.08904  -0.0117   1.0000   0.0525
  -7.250  -0.4033   0.09079   0.08566  -0.0203   1.0000   0.0528
  -7.000  -0.3901   0.08688   0.08175  -0.0247   1.0000   0.0531
  -6.750  -0.3812   0.08317   0.07810  -0.0215   1.0000   0.0537
  -6.500  -0.3698   0.08003   0.07500  -0.0211   1.0000   0.0549
  -6.250  -0.3563   0.07695   0.07193  -0.0230   1.0000   0.0565
  -6.000  -0.3405   0.07372   0.06870  -0.0266   1.0000   0.0586
  -5.750  -0.3111   0.07031   0.06508  -0.0375   1.0000   0.0612
  -5.500  -0.2932   0.06661   0.06131  -0.0406   1.0000   0.0618
  -5.250  -0.2847   0.06332   0.05814  -0.0389   1.0000   0.0624
  -5.000  -0.2745   0.06067   0.05555  -0.0380   1.0000   0.0634
  -4.750  -0.2632   0.05827   0.05316  -0.0378   1.0000   0.0646
  -4.500  -0.2483   0.05583   0.05070  -0.0386   0.9989   0.0664
  -4.250  -0.1937   0.05208   0.04642  -0.0490   0.9901   0.0724
  -4.000  -0.1689   0.04841   0.04291  -0.0508   0.9838   0.0746
  -3.750  -0.1174   0.04743   0.04130  -0.0576   0.9753   0.0848
  -3.500  -0.0928   0.04255   0.03664  -0.0597   0.9679   0.0867
  -3.250  -0.0614   0.03993   0.03403  -0.0622   0.9604   0.0900
  -3.000  -0.0233   0.03775   0.03151  -0.0658   0.9509   0.1012
  -2.750   0.0072   0.03535   0.02915  -0.0676   0.9426   0.1054
  -2.500   0.0404   0.03343   0.02704  -0.0698   0.9322   0.1190
  -2.250   0.0848   0.02969   0.02259  -0.0713   0.9211   0.0691
  -2.000   0.1212   0.02755   0.01989  -0.0721   0.9080   0.0608
  -1.750   0.1509   0.02566   0.01788  -0.0725   0.8919   0.0587
  -1.500   0.1809   0.02405   0.01596  -0.0722   0.8744   0.0562
  -1.250   0.2107   0.02270   0.01416  -0.0715   0.8569   0.0540
  -0.750   0.2659   0.02098   0.01179  -0.0696   0.8232   0.0530
  -0.500   0.2917   0.01995   0.01075  -0.0690   0.8069   0.0544
  -0.250   0.3184   0.01929   0.01002  -0.0683   0.7916   0.0563
   0.000   0.3455   0.01865   0.00927  -0.0677   0.7767   0.0572
   0.250   0.3726   0.01803   0.00856  -0.0670   0.7609   0.0575
   0.500   0.3994   0.01747   0.00794  -0.0662   0.7436   0.0580
   0.750   0.4258   0.01697   0.00739  -0.0654   0.7246   0.0588
   1.000   0.4521   0.01654   0.00691  -0.0645   0.7031   0.0600
   1.250   0.4777   0.01610   0.00645  -0.0636   0.6793   0.0628
   1.500   0.5031   0.01576   0.00607  -0.0626   0.6569   0.0659
   1.750   0.5291   0.01554   0.00578  -0.0617   0.6354   0.0680
   2.000   0.5554   0.01544   0.00556  -0.0610   0.6126   0.0705
   2.250   0.5822   0.01536   0.00539  -0.0604   0.5864   0.0746
   2.500   0.6089   0.01534   0.00532  -0.0598   0.5501   0.0828
   2.750   0.6339   0.01548   0.00516  -0.0589   0.4714   0.0928
   3.000   0.6543   0.01409   0.00521  -0.0575   0.3922   1.0000
   3.250   0.6784   0.01479   0.00540  -0.0568   0.3256   1.0000
   3.500   0.7031   0.01542   0.00563  -0.0563   0.2842   1.0000
   3.750   0.7283   0.01595   0.00591  -0.0559   0.2625   1.0000
   4.000   0.7538   0.01643   0.00624  -0.0554   0.2489   1.0000
   4.250   0.7793   0.01687   0.00660  -0.0550   0.2373   1.0000
   4.500   0.8046   0.01733   0.00696  -0.0546   0.2238   1.0000
   4.750   0.8300   0.01778   0.00735  -0.0542   0.2133   1.0000
   5.000   0.8553   0.01822   0.00776  -0.0538   0.2031   1.0000
   5.250   0.8810   0.01860   0.00816  -0.0534   0.1905   1.0000
   5.500   0.9064   0.01900   0.00854  -0.0530   0.1731   1.0000
   5.750   0.9318   0.01941   0.00893  -0.0526   0.1519   1.0000
   6.000   0.9537   0.02042   0.00942  -0.0520   0.0764   1.0000
   6.250   0.9759   0.02146   0.01035  -0.0513   0.0647   1.0000
   6.500   0.9987   0.02236   0.01126  -0.0506   0.0596   1.0000
   6.750   1.0215   0.02323   0.01219  -0.0499   0.0570   1.0000
   7.000   1.0443   0.02404   0.01310  -0.0492   0.0551   1.0000
   7.250   1.0664   0.02492   0.01408  -0.0484   0.0535   1.0000
   7.500   1.0876   0.02588   0.01515  -0.0476   0.0522   1.0000
   7.750   1.1077   0.02693   0.01628  -0.0467   0.0510   1.0000
   8.000   1.1259   0.02817   0.01757  -0.0457   0.0497   1.0000
   8.250   1.1449   0.02927   0.01877  -0.0446   0.0486   1.0000
   8.500   1.1636   0.03039   0.02002  -0.0435   0.0474   1.0000
   8.750   1.1815   0.03161   0.02133  -0.0424   0.0465   1.0000
   9.000   1.1990   0.03291   0.02271  -0.0412   0.0458   1.0000
   9.250   1.2166   0.03428   0.02414  -0.0401   0.0452   1.0000
   9.500   1.2343   0.03571   0.02566  -0.0389   0.0446   1.0000
   9.750   1.2521   0.03723   0.02723  -0.0379   0.0438   1.0000
  10.000   1.2700   0.03889   0.02889  -0.0370   0.0429   1.0000
  10.250   1.2896   0.04097   0.03090  -0.0363   0.0419   1.0000
  10.500   1.3050   0.04262   0.03283  -0.0351   0.0413   1.0000
  10.750   1.3203   0.04453   0.03498  -0.0339   0.0408   1.0000
  11.000   1.3338   0.04661   0.03731  -0.0326   0.0404   1.0000
  11.250   1.3445   0.04884   0.03981  -0.0312   0.0399   1.0000
  11.500   1.3518   0.05117   0.04241  -0.0296   0.0393   1.0000
  11.750   1.3559   0.05358   0.04507  -0.0279   0.0387   1.0000
  12.000   1.3558   0.05598   0.04771  -0.0259   0.0381   1.0000
  12.250   1.3537   0.05855   0.05049  -0.0240   0.0376   1.0000
  12.500   1.3500   0.06135   0.05349  -0.0226   0.0371   1.0000
  12.750   1.3436   0.06452   0.05687  -0.0215   0.0368   1.0000
  13.000   1.3338   0.06813   0.06072  -0.0210   0.0367   1.0000
  13.250   1.3209   0.07224   0.06506  -0.0212   0.0366   1.0000
  13.500   1.3048   0.07697   0.07004  -0.0221   0.0365   1.0000
  13.750   1.2840   0.08263   0.07597  -0.0243   0.0365   1.0000
  14.000   1.2574   0.08969   0.08331  -0.0280   0.0366   1.0000
  14.250   1.2226   0.09904   0.09297  -0.0342   0.0369   1.0000
  14.500   1.1713   0.11369   0.10795  -0.0452   0.0375   1.0000
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