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OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: OAF128 AIRFOIL (oaf128-il)
Reynolds number: 500,000
Max Cl/Cd: 74.12 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf128-il-500000.txt
Download as CSV file: xf-oaf128-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -1.1258   0.11295   0.10971   0.0269   1.0000   0.0233
 -16.250  -1.1647   0.10079   0.09730   0.0190   1.0000   0.0232
 -16.000  -1.1886   0.09226   0.08859   0.0137   1.0000   0.0232
 -15.750  -1.2090   0.08486   0.08104   0.0092   1.0000   0.0232
 -15.500  -1.2254   0.07842   0.07446   0.0053   1.0000   0.0232
 -15.250  -1.2391   0.07248   0.06838   0.0017   1.0000   0.0233
 -15.000  -1.2502   0.06703   0.06280  -0.0016   1.0000   0.0234
 -14.750  -1.2593   0.06191   0.05754  -0.0047   1.0000   0.0235
 -14.500  -1.2654   0.05726   0.05277  -0.0076   1.0000   0.0237
 -14.250  -1.2696   0.05293   0.04831  -0.0104   1.0000   0.0239
 -14.000  -1.2720   0.04886   0.04411  -0.0131   1.0000   0.0240
 -13.750  -1.2728   0.04510   0.04022  -0.0156   1.0000   0.0242
 -13.500  -1.2726   0.04168   0.03666  -0.0177   1.0000   0.0244
 -13.250  -1.2728   0.03867   0.03350  -0.0191   1.0000   0.0246
 -13.000  -1.2704   0.03630   0.03098  -0.0195   1.0000   0.0248
 -12.750  -1.2604   0.03442   0.02895  -0.0194   1.0000   0.0251
 -12.500  -1.2464   0.03281   0.02719  -0.0194   1.0000   0.0253
 -12.250  -1.2304   0.03127   0.02551  -0.0192   1.0000   0.0256
 -12.000  -1.2157   0.02928   0.02349  -0.0189   1.0000   0.0260
 -11.750  -1.1967   0.02791   0.02209  -0.0188   1.0000   0.0265
 -11.500  -1.1757   0.02675   0.02089  -0.0188   1.0000   0.0269
 -11.250  -1.1534   0.02567   0.01976  -0.0188   1.0000   0.0274
 -11.000  -1.1303   0.02465   0.01866  -0.0189   1.0000   0.0280
 -10.750  -1.1062   0.02369   0.01762  -0.0190   1.0000   0.0286
 -10.500  -1.0812   0.02285   0.01668  -0.0191   1.0000   0.0292
 -10.250  -1.0575   0.02161   0.01540  -0.0192   1.0000   0.0299
 -10.000  -1.0321   0.02066   0.01445  -0.0195   1.0000   0.0308
  -9.750  -1.0056   0.01992   0.01367  -0.0197   1.0000   0.0318
  -9.500  -0.9784   0.01922   0.01292  -0.0200   1.0000   0.0328
  -9.250  -0.9507   0.01861   0.01223  -0.0202   1.0000   0.0336
  -9.000  -0.9240   0.01754   0.01116  -0.0207   1.0000   0.0350
  -8.750  -0.8958   0.01689   0.01050  -0.0211   1.0000   0.0363
  -8.500  -0.8672   0.01633   0.00989  -0.0214   1.0000   0.0379
  -8.250  -0.8386   0.01557   0.00912  -0.0219   1.0000   0.0399
  -8.000  -0.8095   0.01503   0.00857  -0.0223   1.0000   0.0423
  -7.750  -0.7803   0.01440   0.00793  -0.0228   1.0000   0.0454
  -7.500  -0.7507   0.01388   0.00741  -0.0232   1.0000   0.0495
  -7.250  -0.7210   0.01326   0.00684  -0.0238   1.0000   0.0563
  -7.000  -0.6911   0.01265   0.00632  -0.0244   1.0000   0.0695
  -6.750  -0.6611   0.01213   0.00593  -0.0249   1.0000   0.0890
  -6.500  -0.6310   0.01172   0.00561  -0.0255   1.0000   0.1047
  -6.250  -0.6007   0.01139   0.00533  -0.0260   1.0000   0.1167
  -6.000  -0.5703   0.01108   0.00506  -0.0265   1.0000   0.1278
  -5.750  -0.5398   0.01078   0.00481  -0.0270   1.0000   0.1395
  -5.500  -0.5091   0.01049   0.00459  -0.0275   1.0000   0.1525
  -5.250  -0.4782   0.01022   0.00439  -0.0281   1.0000   0.1672
  -5.000  -0.4472   0.00998   0.00422  -0.0287   1.0000   0.1825
  -4.750  -0.4173   0.01002   0.00424  -0.0288   0.9365   0.1968
  -4.500  -0.3928   0.00995   0.00416  -0.0277   0.9020   0.2104
  -4.250  -0.3666   0.00986   0.00403  -0.0269   0.8735   0.2246
  -4.000  -0.3388   0.00974   0.00392  -0.0266   0.8468   0.2445
  -3.750  -0.3105   0.00964   0.00380  -0.0264   0.8209   0.2651
  -3.500  -0.2816   0.00956   0.00368  -0.0263   0.7953   0.2823
  -3.250  -0.2523   0.00949   0.00357  -0.0263   0.7689   0.2990
  -3.000  -0.2229   0.00946   0.00347  -0.0264   0.7438   0.3158
  -2.750  -0.1931   0.00942   0.00339  -0.0265   0.7203   0.3319
  -2.500  -0.1632   0.00938   0.00331  -0.0266   0.6974   0.3470
  -2.250  -0.1333   0.00937   0.00324  -0.0268   0.6743   0.3615
  -2.000  -0.1033   0.00937   0.00318  -0.0270   0.6507   0.3748
  -1.500  -0.0431   0.00939   0.00308  -0.0274   0.6103   0.4011
  -1.250  -0.0129   0.00939   0.00305  -0.0276   0.5922   0.4136
  -1.000   0.0173   0.00941   0.00302  -0.0278   0.5757   0.4263
  -0.750   0.0475   0.00941   0.00301  -0.0280   0.5606   0.4405
  -0.500   0.0777   0.00941   0.00301  -0.0283   0.5470   0.4559
  -0.250   0.1079   0.00942   0.00301  -0.0285   0.5338   0.4708
   0.000   0.1381   0.00942   0.00301  -0.0287   0.5210   0.4847
   0.250   0.1683   0.00944   0.00302  -0.0290   0.5086   0.4996
   0.500   0.1985   0.00945   0.00304  -0.0292   0.4964   0.5149
   0.750   0.2288   0.00944   0.00307  -0.0295   0.4853   0.5309
   1.000   0.2590   0.00946   0.00310  -0.0297   0.4744   0.5489
   1.250   0.2891   0.00946   0.00314  -0.0299   0.4628   0.5688
   1.500   0.3193   0.00946   0.00319  -0.0302   0.4520   0.5911
   1.750   0.3494   0.00948   0.00325  -0.0304   0.4412   0.6170
   2.000   0.3794   0.00945   0.00332  -0.0306   0.4296   0.6477
   2.250   0.4092   0.00944   0.00339  -0.0308   0.4148   0.6829
   2.500   0.4386   0.00943   0.00347  -0.0308   0.3990   0.7234
   2.750   0.4675   0.00944   0.00357  -0.0308   0.3854   0.7681
   3.000   0.4957   0.00940   0.00367  -0.0304   0.3727   0.8129
   3.250   0.5226   0.00939   0.00375  -0.0298   0.3600   0.8584
   3.500   0.5463   0.00933   0.00377  -0.0284   0.3475   0.9109
   3.750   0.5716   0.00919   0.00365  -0.0275   0.3336   1.0000
   4.000   0.6021   0.00936   0.00376  -0.0279   0.3190   1.0000
   4.250   0.6325   0.00956   0.00389  -0.0283   0.3038   1.0000
   4.500   0.6628   0.00977   0.00403  -0.0286   0.2886   1.0000
   4.750   0.6929   0.00999   0.00419  -0.0290   0.2733   1.0000
   5.000   0.7229   0.01024   0.00436  -0.0294   0.2574   1.0000
   5.250   0.7528   0.01050   0.00455  -0.0297   0.2423   1.0000
   5.500   0.7825   0.01079   0.00476  -0.0300   0.2274   1.0000
   5.750   0.8121   0.01109   0.00500  -0.0303   0.2124   1.0000
   6.000   0.8415   0.01141   0.00524  -0.0306   0.1964   1.0000
   6.250   0.8709   0.01175   0.00551  -0.0309   0.1762   1.0000
   6.500   0.8998   0.01221   0.00582  -0.0313   0.1520   1.0000
   6.750   0.9285   0.01273   0.00620  -0.0316   0.1313   1.0000
   7.000   0.9571   0.01325   0.00663  -0.0319   0.1177   1.0000
   7.250   0.9856   0.01371   0.00704  -0.0321   0.1086   1.0000
   7.500   1.0138   0.01421   0.00751  -0.0323   0.1016   1.0000
   7.750   1.0421   0.01465   0.00794  -0.0324   0.0962   1.0000
   8.000   1.0698   0.01520   0.00847  -0.0326   0.0912   1.0000
   8.250   1.0978   0.01560   0.00889  -0.0326   0.0875   1.0000
   8.500   1.1249   0.01619   0.00945  -0.0327   0.0836   1.0000
   8.750   1.1521   0.01669   0.00998  -0.0328   0.0805   1.0000
   9.000   1.1794   0.01712   0.01045  -0.0328   0.0776   1.0000
   9.250   1.2057   0.01772   0.01104  -0.0328   0.0748   1.0000
   9.500   1.2314   0.01840   0.01173  -0.0327   0.0722   1.0000
   9.750   1.2579   0.01884   0.01224  -0.0326   0.0700   1.0000
  10.000   1.2838   0.01937   0.01279  -0.0325   0.0678   1.0000
  10.250   1.3074   0.02024   0.01364  -0.0323   0.0654   1.0000
  10.500   1.3323   0.02083   0.01430  -0.0320   0.0637   1.0000
  10.750   1.3572   0.02138   0.01490  -0.0318   0.0619   1.0000
  11.000   1.3813   0.02198   0.01554  -0.0315   0.0601   1.0000
  11.250   1.4026   0.02290   0.01645  -0.0311   0.0583   1.0000
  11.500   1.4243   0.02373   0.01735  -0.0306   0.0568   1.0000
  11.750   1.4468   0.02439   0.01809  -0.0301   0.0553   1.0000
  12.000   1.4682   0.02510   0.01885  -0.0296   0.0538   1.0000
  12.250   1.4877   0.02595   0.01973  -0.0290   0.0524   1.0000
  12.500   1.5010   0.02737   0.02115  -0.0279   0.0509   1.0000
  12.750   1.5196   0.02815   0.02206  -0.0271   0.0499   1.0000
  13.000   1.5352   0.02910   0.02310  -0.0261   0.0487   1.0000
  13.250   1.5480   0.03016   0.02424  -0.0250   0.0476   1.0000
  13.500   1.5546   0.03150   0.02563  -0.0234   0.0467   1.0000
  13.750   1.5562   0.03353   0.02771  -0.0224   0.0458   1.0000
  14.000   1.5552   0.03621   0.03046  -0.0220   0.0450   1.0000
  14.250   1.5622   0.03838   0.03278  -0.0224   0.0443   1.0000
  14.500   1.5673   0.04090   0.03542  -0.0230   0.0435   1.0000
  14.750   1.5711   0.04368   0.03831  -0.0238   0.0426   1.0000
  15.000   1.5734   0.04671   0.04143  -0.0249   0.0419   1.0000
  15.250   1.5740   0.05003   0.04482  -0.0261   0.0412   1.0000
  15.500   1.5711   0.05374   0.04859  -0.0273   0.0406   1.0000
  15.750   1.5642   0.05778   0.05267  -0.0283   0.0399   1.0000
  16.000   1.5592   0.06186   0.05688  -0.0297   0.0394   1.0000
  16.250   1.5536   0.06611   0.06129  -0.0314   0.0389   1.0000
  16.500   1.5467   0.07056   0.06586  -0.0331   0.0384   1.0000
  16.750   1.5386   0.07514   0.07056  -0.0348   0.0378   1.0000
  17.000   1.5305   0.07985   0.07537  -0.0367   0.0373   1.0000
  17.250   1.5228   0.08463   0.08024  -0.0387   0.0368   1.0000
  17.500   1.5151   0.08947   0.08515  -0.0408   0.0363   1.0000
  17.750   1.5076   0.09430   0.09005  -0.0428   0.0358   1.0000
  18.000   1.5016   0.09870   0.09446  -0.0444   0.0352   1.0000
  18.250   1.4921   0.10389   0.09975  -0.0467   0.0348   1.0000
  18.500   1.4802   0.10990   0.10591  -0.0497   0.0344   1.0000
  18.750   1.4685   0.11592   0.11208  -0.0527   0.0340   1.0000
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