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OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: OAF128 AIRFOIL (oaf128-il)
Reynolds number: 100,000
Max Cl/Cd: 41.44 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf128-il-100000.txt
Download as CSV file: xf-oaf128-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF128 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8660   0.07826   0.07293  -0.0052   1.0000   0.0784
 -10.750  -0.8977   0.06900   0.06355  -0.0129   1.0000   0.0775
 -10.500  -0.9295   0.06145   0.05572  -0.0183   1.0000   0.0766
 -10.250  -0.9473   0.05474   0.04856  -0.0214   1.0000   0.0764
 -10.000  -0.9510   0.04911   0.04240  -0.0233   1.0000   0.0767
  -9.750  -0.9445   0.04439   0.03708  -0.0244   1.0000   0.0775
  -9.500  -0.9313   0.04043   0.03246  -0.0252   1.0000   0.0787
  -9.250  -0.9093   0.03810   0.03016  -0.0254   1.0000   0.0811
  -9.000  -0.8860   0.03628   0.02824  -0.0256   1.0000   0.0843
  -8.750  -0.8634   0.03381   0.02526  -0.0260   1.0000   0.0878
  -8.500  -0.8386   0.03173   0.02320  -0.0261   1.0000   0.0912
  -8.250  -0.8128   0.03017   0.02150  -0.0263   1.0000   0.0964
  -8.000  -0.7869   0.02847   0.01976  -0.0265   1.0000   0.1025
  -7.750  -0.7597   0.02703   0.01803  -0.0267   1.0000   0.1108
  -7.500  -0.7331   0.02562   0.01679  -0.0269   1.0000   0.1209
  -7.250  -0.7057   0.02430   0.01549  -0.0272   1.0000   0.1351
  -7.000  -0.6781   0.02317   0.01445  -0.0276   1.0000   0.1528
  -6.750  -0.6500   0.02247   0.01387  -0.0280   1.0000   0.1721
  -6.500  -0.6212   0.02181   0.01318  -0.0284   1.0000   0.1925
  -6.250  -0.5922   0.02114   0.01246  -0.0289   1.0000   0.2120
  -6.000  -0.5633   0.02054   0.01192  -0.0293   1.0000   0.2303
  -5.750  -0.5343   0.02009   0.01158  -0.0296   1.0000   0.2484
  -5.500  -0.5050   0.01972   0.01131  -0.0299   1.0000   0.2671
  -5.250  -0.4755   0.01934   0.01102  -0.0303   1.0000   0.2858
  -5.000  -0.4458   0.01894   0.01067  -0.0306   1.0000   0.3043
  -4.750  -0.4159   0.01854   0.01034  -0.0309   1.0000   0.3229
  -4.500  -0.3858   0.01816   0.01001  -0.0313   1.0000   0.3417
  -4.250  -0.3557   0.01781   0.00973  -0.0318   1.0000   0.3606
  -4.000  -0.3254   0.01747   0.00946  -0.0322   1.0000   0.3794
  -3.750  -0.2950   0.01716   0.00923  -0.0328   1.0000   0.3984
  -3.500  -0.2645   0.01685   0.00902  -0.0334   1.0000   0.4175
  -3.250  -0.2343   0.01658   0.00885  -0.0342   1.0000   0.4367
  -3.000  -0.2056   0.01636   0.00875  -0.0350   1.0000   0.4556
  -2.750  -0.1819   0.01633   0.00885  -0.0355   0.9966   0.4731
  -2.500  -0.1268   0.01616   0.00867  -0.0409   0.9708   0.4999
  -2.250  -0.0826   0.01609   0.00870  -0.0435   0.9389   0.5225
  -2.000  -0.0544   0.01622   0.00883  -0.0427   0.9039   0.5421
  -1.750  -0.0322   0.01633   0.00891  -0.0405   0.8731   0.5600
  -1.500  -0.0090   0.01636   0.00891  -0.0388   0.8442   0.5777
  -1.250   0.0138   0.01637   0.00890  -0.0369   0.8199   0.5951
  -1.000   0.0377   0.01634   0.00886  -0.0353   0.7973   0.6126
  -0.750   0.0630   0.01630   0.00883  -0.0341   0.7753   0.6309
  -0.500   0.0884   0.01628   0.00880  -0.0329   0.7547   0.6511
  -0.250   0.1141   0.01625   0.00876  -0.0318   0.7347   0.6728
   0.000   0.1391   0.01620   0.00875  -0.0304   0.7153   0.6949
   0.250   0.1639   0.01617   0.00874  -0.0290   0.6966   0.7200
   0.500   0.1887   0.01615   0.00874  -0.0276   0.6793   0.7499
   0.750   0.2116   0.01613   0.00875  -0.0256   0.6640   0.7827
   1.000   0.2337   0.01606   0.00876  -0.0235   0.6482   0.8203
   1.250   0.2527   0.01590   0.00870  -0.0207   0.6332   0.8648
   1.500   0.2713   0.01556   0.00843  -0.0177   0.6192   0.9303
   1.750   0.3122   0.01550   0.00825  -0.0206   0.6028   1.0000
   2.000   0.3468   0.01580   0.00831  -0.0223   0.5883   1.0000
   2.250   0.3796   0.01608   0.00848  -0.0235   0.5724   1.0000
   2.500   0.4113   0.01639   0.00869  -0.0243   0.5567   1.0000
   2.750   0.4422   0.01672   0.00893  -0.0248   0.5418   1.0000
   3.000   0.4724   0.01705   0.00914  -0.0251   0.5275   1.0000
   3.250   0.5020   0.01737   0.00929  -0.0252   0.5136   1.0000
   3.500   0.5322   0.01767   0.00957  -0.0255   0.4973   1.0000
   3.750   0.5618   0.01793   0.00978  -0.0257   0.4803   1.0000
   4.000   0.5911   0.01816   0.00993  -0.0257   0.4626   1.0000
   4.250   0.6202   0.01839   0.01009  -0.0257   0.4451   1.0000
   4.500   0.6493   0.01864   0.01028  -0.0258   0.4280   1.0000
   4.750   0.6783   0.01892   0.01050  -0.0258   0.4113   1.0000
   5.000   0.7072   0.01920   0.01074  -0.0258   0.3947   1.0000
   5.250   0.7359   0.01948   0.01097  -0.0258   0.3778   1.0000
   5.500   0.7645   0.01976   0.01121  -0.0258   0.3604   1.0000
   5.750   0.7928   0.02005   0.01147  -0.0258   0.3421   1.0000
   6.000   0.8209   0.02036   0.01173  -0.0258   0.3226   1.0000
   6.250   0.8487   0.02071   0.01199  -0.0257   0.3019   1.0000
   6.500   0.8759   0.02119   0.01236  -0.0256   0.2799   1.0000
   6.750   0.9029   0.02179   0.01293  -0.0256   0.2551   1.0000
   7.000   0.9292   0.02255   0.01350  -0.0255   0.2337   1.0000
   7.250   0.9552   0.02355   0.01434  -0.0254   0.2151   1.0000
   7.500   0.9811   0.02458   0.01527  -0.0253   0.1995   1.0000
   7.750   1.0071   0.02554   0.01627  -0.0252   0.1863   1.0000
   8.000   1.0328   0.02664   0.01745  -0.0251   0.1754   1.0000
   8.250   1.0583   0.02781   0.01853  -0.0249   0.1670   1.0000
   8.500   1.0836   0.02889   0.01969  -0.0247   0.1588   1.0000
   8.750   1.1085   0.03025   0.02103  -0.0245   0.1524   1.0000
   9.000   1.1328   0.03153   0.02246  -0.0242   0.1460   1.0000
   9.250   1.1581   0.03303   0.02375  -0.0241   0.1408   1.0000
   9.500   1.1798   0.03462   0.02575  -0.0237   0.1357   1.0000
   9.750   1.2028   0.03607   0.02728  -0.0233   0.1311   1.0000
  10.000   1.2262   0.03801   0.02913  -0.0232   0.1272   1.0000
  10.250   1.2431   0.04012   0.03171  -0.0225   0.1234   1.0000
  10.500   1.2619   0.04207   0.03386  -0.0220   0.1198   1.0000
  10.750   1.2838   0.04381   0.03555  -0.0217   0.1165   1.0000
  11.000   1.2962   0.04679   0.03883  -0.0211   0.1139   1.0000
  11.250   1.3000   0.05008   0.04264  -0.0201   0.1116   1.0000
  11.500   1.3025   0.05336   0.04629  -0.0191   0.1094   1.0000
  11.750   1.3103   0.05601   0.04911  -0.0184   0.1071   1.0000
  12.000   1.3293   0.05798   0.05101  -0.0180   0.1045   1.0000
  12.250   1.3280   0.06220   0.05541  -0.0173   0.1031   1.0000
  12.500   1.3017   0.06700   0.06063  -0.0161   0.1028   1.0000
  12.750   1.2676   0.07228   0.06620  -0.0157   0.1028   1.0000
  13.000   1.2296   0.07950   0.07367  -0.0184   0.1031   1.0000
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