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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 100,000
Max Cl/Cd: 56.57 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe335-il-100000.txt
Download as CSV file: xf-goe335-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3195   0.09184   0.08727  -0.0231   1.0000   0.0580
  -7.000  -0.3217   0.08979   0.08531  -0.0231   1.0000   0.0599
  -6.750  -0.3220   0.08811   0.08372  -0.0256   1.0000   0.0621
  -6.500  -0.3188   0.08731   0.08297  -0.0318   1.0000   0.0633
  -6.250  -0.3101   0.08617   0.08179  -0.0377   1.0000   0.0638
  -6.000  -0.3153   0.07984   0.07565  -0.0290   1.0000   0.0655
  -5.750  -0.3143   0.07712   0.07298  -0.0261   1.0000   0.0675
  -5.500  -0.3142   0.07494   0.07085  -0.0250   1.0000   0.0696
  -5.250  -0.3143   0.07292   0.06887  -0.0246   1.0000   0.0720
  -5.000  -0.3087   0.07103   0.06696  -0.0267   1.0000   0.0754
  -4.750  -0.2877   0.06897   0.06469  -0.0346   1.0000   0.0781
  -4.500  -0.2914   0.06534   0.06120  -0.0304   1.0000   0.0794
  -4.250  -0.2880   0.06282   0.05872  -0.0283   1.0000   0.0820
  -4.000  -0.2758   0.06038   0.05624  -0.0291   1.0000   0.0867
  -3.750  -0.2359   0.05623   0.05188  -0.0370   0.9963   0.0940
  -3.500  -0.1844   0.05185   0.04728  -0.0453   0.9872   0.1083
  -3.250  -0.1356   0.04783   0.04304  -0.0524   0.9784   0.1225
  -3.000  -0.0895   0.04411   0.03916  -0.0583   0.9708   0.1378
  -2.750  -0.0461   0.04154   0.03627  -0.0635   0.9617   0.1638
  -2.500  -0.0058   0.03836   0.03304  -0.0674   0.9557   0.1935
  -2.250   0.0263   0.03586   0.03045  -0.0694   0.9460   0.2233
  -2.000   0.0611   0.03347   0.02802  -0.0716   0.9380   0.2673
  -1.500   0.1834   0.02591   0.01843  -0.0814   0.9247   0.1166
  -1.250   0.2292   0.02378   0.01560  -0.0836   0.9169   0.1046
  -1.000   0.2705   0.02225   0.01373  -0.0855   0.9078   0.1068
  -0.750   0.3196   0.02075   0.01194  -0.0886   0.9012   0.1058
  -0.500   0.3571   0.01935   0.01049  -0.0898   0.8903   0.1079
  -0.250   0.3960   0.01827   0.00940  -0.0911   0.8796   0.1133
   0.000   0.4348   0.01730   0.00848  -0.0924   0.8684   0.1273
   0.250   0.4716   0.01637   0.00760  -0.0931   0.8561   0.1456
   0.500   0.5226   0.01340   0.00652  -0.0964   0.8444   1.0000
   0.750   0.5517   0.01338   0.00623  -0.0957   0.8256   1.0000
   1.000   0.5803   0.01339   0.00602  -0.0950   0.8054   1.0000
   1.250   0.6072   0.01345   0.00590  -0.0939   0.7839   1.0000
   1.500   0.6325   0.01355   0.00583  -0.0926   0.7601   1.0000
   1.750   0.6564   0.01367   0.00578  -0.0911   0.7333   1.0000
   2.000   0.6803   0.01377   0.00572  -0.0896   0.7052   1.0000
   2.250   0.7043   0.01391   0.00568  -0.0882   0.6768   1.0000
   2.500   0.7286   0.01412   0.00573  -0.0870   0.6496   1.0000
   2.750   0.7532   0.01439   0.00582  -0.0860   0.6254   1.0000
   3.000   0.7780   0.01469   0.00596  -0.0852   0.6041   1.0000
   3.250   0.8030   0.01504   0.00617  -0.0844   0.5854   1.0000
   3.500   0.8280   0.01543   0.00650  -0.0837   0.5688   1.0000
   3.750   0.8534   0.01583   0.00683  -0.0832   0.5547   1.0000
   4.000   0.8790   0.01625   0.00719  -0.0827   0.5421   1.0000
   4.250   0.9046   0.01667   0.00754  -0.0822   0.5300   1.0000
   4.500   0.9296   0.01709   0.00798  -0.0816   0.5175   1.0000
   4.750   0.9542   0.01753   0.00844  -0.0809   0.5052   1.0000
   5.000   0.9791   0.01802   0.00898  -0.0804   0.4945   1.0000
   5.250   1.0048   0.01856   0.00953  -0.0800   0.4857   1.0000
   5.500   1.0300   0.01910   0.01014  -0.0795   0.4764   1.0000
   5.750   1.0543   0.01966   0.01086  -0.0789   0.4665   1.0000
   6.000   1.0790   0.02022   0.01147  -0.0784   0.4562   1.0000
   6.250   1.1041   0.02076   0.01202  -0.0778   0.4452   1.0000
   6.500   1.1260   0.02114   0.01250  -0.0766   0.4290   1.0000
   6.750   1.1463   0.02137   0.01283  -0.0751   0.4088   1.0000
   7.000   1.1678   0.02160   0.01308  -0.0737   0.3904   1.0000
   7.250   1.1875   0.02178   0.01337  -0.0722   0.3710   1.0000
   7.500   1.2050   0.02176   0.01349  -0.0701   0.3477   1.0000
   7.750   1.2179   0.02153   0.01343  -0.0673   0.3126   1.0000
   8.000   1.2243   0.02172   0.01343  -0.0636   0.2072   1.0000
   8.250   1.2130   0.02556   0.01598  -0.0589   0.0781   1.0000
   8.500   1.2154   0.02789   0.01832  -0.0555   0.0633   1.0000
   8.750   1.2228   0.02952   0.02013  -0.0525   0.0566   1.0000
   9.000   1.2239   0.03145   0.02211  -0.0492   0.0527   1.0000
   9.250   1.2273   0.03305   0.02383  -0.0459   0.0493   1.0000
   9.500   1.2319   0.03465   0.02553  -0.0430   0.0461   1.0000
   9.750   1.2369   0.03649   0.02738  -0.0404   0.0438   1.0000
  10.000   1.2492   0.03881   0.02963  -0.0386   0.0421   1.0000
  10.250   1.2862   0.04209   0.03294  -0.0394   0.0408   1.0000
  10.500   1.3191   0.04543   0.03653  -0.0398   0.0404   1.0000
  10.750   1.3377   0.04852   0.03994  -0.0388   0.0398   1.0000
  11.000   1.3461   0.05133   0.04310  -0.0367   0.0390   1.0000
  11.250   1.3481   0.05420   0.04632  -0.0342   0.0383   1.0000
  11.500   1.3464   0.05740   0.04986  -0.0315   0.0382   1.0000
  11.750   1.3412   0.06092   0.05370  -0.0291   0.0386   1.0000
  12.000   1.3323   0.06466   0.05774  -0.0268   0.0390   1.0000
  12.250   1.3214   0.06862   0.06197  -0.0252   0.0394   1.0000
  12.500   1.3075   0.07293   0.06654  -0.0242   0.0398   1.0000
  12.750   1.2928   0.07763   0.07146  -0.0239   0.0402   1.0000
  13.000   1.2778   0.08281   0.07685  -0.0242   0.0406   1.0000
  13.250   1.2715   0.08871   0.08293  -0.0248   0.0414   1.0000
  13.500   1.2521   0.09276   0.08721  -0.0262   0.0418   1.0000
  13.750   1.2283   0.09812   0.09280  -0.0291   0.0422   1.0000
  14.000   1.2010   0.10493   0.09984  -0.0335   0.0425   1.0000
  14.250   1.1706   0.11332   0.10845  -0.0396   0.0429   1.0000
  14.500   1.1345   0.12420   0.11951  -0.0482   0.0433   1.0000
  14.750   1.0650   0.14824   0.14363  -0.0660   0.0490   1.0000
  15.000   1.0579   0.15626   0.15163  -0.0698   0.0507   1.0000
  15.250   1.0585   0.16197   0.15733  -0.0716   0.0517   1.0000
  15.500   0.8552   0.16785   0.16373  -0.0706   0.0635   1.0000
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