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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 500,000
Max Cl/Cd: 84.41 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf117-il-500000.txt
Download as CSV file: xf-oaf117-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF117 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -1.0533   0.08980   0.08684   0.0067   1.0000   0.0231
 -14.500  -1.1002   0.07723   0.07405  -0.0018   1.0000   0.0229
 -14.250  -1.1306   0.06794   0.06459  -0.0084   1.0000   0.0229
 -14.000  -1.1522   0.06018   0.05666  -0.0143   1.0000   0.0230
 -13.750  -1.1677   0.05334   0.04966  -0.0199   1.0000   0.0231
 -13.500  -1.1781   0.04715   0.04330  -0.0257   1.0000   0.0232
 -13.250  -1.1858   0.04142   0.03738  -0.0322   1.0000   0.0234
 -13.000  -1.1797   0.03746   0.03319  -0.0372   1.0000   0.0238
 -12.750  -1.1677   0.03493   0.03046  -0.0390   1.0000   0.0244
 -12.500  -1.1518   0.03289   0.02819  -0.0403   1.0000   0.0249
 -12.250  -1.1359   0.03061   0.02571  -0.0412   1.0000   0.0254
 -12.000  -1.1164   0.02895   0.02400  -0.0417   1.0000   0.0261
 -11.750  -1.0933   0.02792   0.02293  -0.0422   1.0000   0.0267
 -11.500  -1.0694   0.02693   0.02186  -0.0427   1.0000   0.0276
 -11.250  -1.0449   0.02591   0.02069  -0.0431   1.0000   0.0285
 -11.000  -1.0196   0.02497   0.01958  -0.0435   1.0000   0.0292
 -10.750  -0.9962   0.02333   0.01785  -0.0440   1.0000   0.0302
 -10.500  -0.9703   0.02246   0.01696  -0.0444   1.0000   0.0310
 -10.250  -0.9434   0.02175   0.01621  -0.0448   1.0000   0.0321
 -10.000  -0.9161   0.02106   0.01541  -0.0451   1.0000   0.0333
  -9.750  -0.8882   0.02047   0.01469  -0.0454   1.0000   0.0342
  -9.500  -0.8620   0.01914   0.01334  -0.0460   1.0000   0.0355
  -9.250  -0.8340   0.01850   0.01268  -0.0464   1.0000   0.0367
  -9.000  -0.8056   0.01793   0.01206  -0.0467   1.0000   0.0381
  -8.750  -0.7768   0.01746   0.01149  -0.0470   1.0000   0.0395
  -8.500  -0.7487   0.01646   0.01047  -0.0476   1.0000   0.0412
  -8.250  -0.7197   0.01590   0.00990  -0.0480   1.0000   0.0428
  -8.000  -0.6905   0.01543   0.00938  -0.0483   1.0000   0.0446
  -7.750  -0.6611   0.01500   0.00888  -0.0487   1.0000   0.0463
  -7.500  -0.6318   0.01421   0.00812  -0.0493   1.0000   0.0488
  -7.250  -0.6021   0.01377   0.00766  -0.0497   1.0000   0.0511
  -7.000  -0.5723   0.01344   0.00727  -0.0500   1.0000   0.0532
  -6.750  -0.5423   0.01275   0.00661  -0.0507   1.0000   0.0569
  -6.500  -0.5122   0.01239   0.00623  -0.0511   1.0000   0.0601
  -6.250  -0.4819   0.01189   0.00573  -0.0517   1.0000   0.0643
  -6.000  -0.4516   0.01152   0.00537  -0.0522   1.0000   0.0692
  -5.750  -0.4211   0.01108   0.00497  -0.0527   1.0000   0.0759
  -5.500  -0.3905   0.01069   0.00463  -0.0533   1.0000   0.0850
  -5.250  -0.3598   0.01031   0.00434  -0.0539   1.0000   0.0991
  -5.000  -0.3291   0.01000   0.00412  -0.0545   1.0000   0.1168
  -4.750  -0.2954   0.00982   0.00398  -0.0557   0.9664   0.1337
  -4.500  -0.2680   0.00977   0.00392  -0.0551   0.9258   0.1482
  -4.000  -0.2160   0.00967   0.00373  -0.0535   0.8681   0.1768
  -3.750  -0.1885   0.00958   0.00360  -0.0531   0.8419   0.1912
  -3.500  -0.1601   0.00949   0.00346  -0.0530   0.8166   0.2063
  -3.250  -0.1313   0.00941   0.00334  -0.0529   0.7927   0.2231
  -3.000  -0.1022   0.00934   0.00323  -0.0529   0.7715   0.2406
  -2.750  -0.0729   0.00927   0.00313  -0.0530   0.7504   0.2595
  -2.500  -0.0433   0.00920   0.00305  -0.0531   0.7285   0.2794
  -2.250  -0.0138   0.00916   0.00298  -0.0532   0.7076   0.3003
  -2.000   0.0159   0.00912   0.00294  -0.0533   0.6894   0.3234
  -1.750   0.0456   0.00910   0.00290  -0.0535   0.6723   0.3440
  -1.500   0.0754   0.00908   0.00286  -0.0536   0.6560   0.3614
  -1.250   0.1052   0.00907   0.00283  -0.0538   0.6405   0.3790
  -1.000   0.1349   0.00907   0.00281  -0.0540   0.6256   0.3956
  -0.750   0.1647   0.00908   0.00279  -0.0541   0.6107   0.4120
   0.000   0.2542   0.00909   0.00280  -0.0547   0.5689   0.4646
   0.250   0.2840   0.00910   0.00282  -0.0548   0.5556   0.4836
   0.500   0.3137   0.00911   0.00285  -0.0550   0.5423   0.5051
   0.750   0.3435   0.00911   0.00288  -0.0552   0.5283   0.5277
   1.250   0.4029   0.00912   0.00296  -0.0556   0.5005   0.5777
   1.500   0.4325   0.00912   0.00302  -0.0557   0.4878   0.6105
   1.750   0.4620   0.00911   0.00309  -0.0559   0.4751   0.6510
   2.000   0.4913   0.00904   0.00318  -0.0559   0.4626   0.7006
   2.250   0.5197   0.00894   0.00328  -0.0558   0.4507   0.7676
   2.500   0.5431   0.00870   0.00331  -0.0543   0.4392   0.8767
   2.750   0.5681   0.00850   0.00318  -0.0532   0.4273   1.0000
   3.000   0.5980   0.00864   0.00327  -0.0535   0.4148   1.0000
   3.250   0.6278   0.00880   0.00337  -0.0537   0.4026   1.0000
   3.500   0.6575   0.00898   0.00347  -0.0539   0.3900   1.0000
   3.750   0.6872   0.00914   0.00359  -0.0542   0.3769   1.0000
   4.000   0.7168   0.00930   0.00372  -0.0544   0.3638   1.0000
   4.250   0.7463   0.00949   0.00385  -0.0546   0.3501   1.0000
   4.500   0.7756   0.00969   0.00400  -0.0547   0.3352   1.0000
   4.750   0.8049   0.00991   0.00415  -0.0549   0.3188   1.0000
   5.000   0.8341   0.01014   0.00432  -0.0551   0.3020   1.0000
   5.250   0.8631   0.01039   0.00450  -0.0553   0.2853   1.0000
   5.500   0.8920   0.01066   0.00471  -0.0555   0.2688   1.0000
   5.750   0.9209   0.01095   0.00494  -0.0556   0.2523   1.0000
   6.000   0.9496   0.01125   0.00518  -0.0558   0.2339   1.0000
   6.250   0.9780   0.01162   0.00544  -0.0559   0.2138   1.0000
   6.500   1.0063   0.01199   0.00574  -0.0561   0.1948   1.0000
   6.750   1.0344   0.01239   0.00606  -0.0562   0.1772   1.0000
   7.000   1.0623   0.01282   0.00641  -0.0563   0.1613   1.0000
   7.250   1.0900   0.01325   0.00679  -0.0564   0.1457   1.0000
   7.500   1.1175   0.01373   0.00719  -0.0565   0.1297   1.0000
   7.750   1.1446   0.01426   0.00763  -0.0565   0.1133   1.0000
   8.000   1.1715   0.01480   0.00810  -0.0565   0.0968   1.0000
   8.250   1.1977   0.01545   0.00865  -0.0565   0.0813   1.0000
   8.500   1.2236   0.01614   0.00926  -0.0564   0.0697   1.0000
   8.750   1.2493   0.01679   0.00989  -0.0563   0.0619   1.0000
   9.000   1.2748   0.01745   0.01056  -0.0561   0.0561   1.0000
   9.250   1.2990   0.01828   0.01136  -0.0558   0.0511   1.0000
   9.500   1.3244   0.01883   0.01197  -0.0556   0.0480   1.0000
   9.750   1.3480   0.01962   0.01275  -0.0552   0.0451   1.0000
  10.000   1.3711   0.02045   0.01363  -0.0548   0.0428   1.0000
  10.250   1.3946   0.02112   0.01437  -0.0543   0.0408   1.0000
  10.500   1.4165   0.02198   0.01524  -0.0538   0.0389   1.0000
  10.750   1.4356   0.02311   0.01642  -0.0530   0.0372   1.0000
  11.000   1.4574   0.02383   0.01722  -0.0524   0.0359   1.0000
  11.250   1.4773   0.02469   0.01815  -0.0516   0.0346   1.0000
  11.500   1.4953   0.02569   0.01919  -0.0507   0.0335   1.0000
  11.750   1.5072   0.02722   0.02075  -0.0492   0.0325   1.0000
  12.000   1.5201   0.02847   0.02210  -0.0478   0.0317   1.0000
  12.250   1.5331   0.02958   0.02332  -0.0463   0.0311   1.0000
  12.500   1.5423   0.03086   0.02470  -0.0446   0.0304   1.0000
  12.750   1.5453   0.03239   0.02633  -0.0424   0.0298   1.0000
  13.000   1.5485   0.03428   0.02830  -0.0411   0.0293   1.0000
  13.250   1.5517   0.03649   0.03059  -0.0405   0.0287   1.0000
  13.500   1.5529   0.03914   0.03332  -0.0404   0.0282   1.0000
  13.750   1.5498   0.04246   0.03671  -0.0405   0.0278   1.0000
  14.000   1.5452   0.04606   0.04040  -0.0407   0.0273   1.0000
  14.250   1.5471   0.04908   0.04355  -0.0413   0.0271   1.0000
  14.500   1.5471   0.05238   0.04698  -0.0421   0.0268   1.0000
  14.750   1.5457   0.05591   0.05064  -0.0429   0.0264   1.0000
  15.000   1.5426   0.05967   0.05452  -0.0438   0.0261   1.0000
  15.250   1.5386   0.06357   0.05854  -0.0448   0.0258   1.0000
  15.500   1.5336   0.06763   0.06271  -0.0459   0.0256   1.0000
  15.750   1.5278   0.07183   0.06701  -0.0471   0.0253   1.0000
  16.000   1.5216   0.07613   0.07142  -0.0484   0.0250   1.0000
  16.250   1.5150   0.08053   0.07591  -0.0498   0.0248   1.0000
  16.500   1.5088   0.08502   0.08049  -0.0513   0.0246   1.0000
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