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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 200,000
Max Cl/Cd: 62.97 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf117-il-200000-n5.txt
Download as CSV file: xf-oaf117-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.9740   0.07513   0.07083  -0.0044   1.0000   0.0277
 -12.750  -1.0119   0.06365   0.05911  -0.0137   1.0000   0.0275
 -12.500  -1.0346   0.05502   0.05024  -0.0216   1.0000   0.0276
 -12.250  -1.0497   0.04793   0.04291  -0.0291   1.0000   0.0278
 -12.000  -1.0518   0.04259   0.03725  -0.0357   1.0000   0.0282
 -11.750  -1.0447   0.03901   0.03331  -0.0385   1.0000   0.0289
 -11.500  -1.0314   0.03633   0.03035  -0.0401   1.0000   0.0296
 -11.250  -1.0126   0.03467   0.02864  -0.0409   1.0000   0.0302
 -10.750  -0.9707   0.03163   0.02535  -0.0424   1.0000   0.0320
 -10.500  -0.9482   0.03007   0.02356  -0.0431   1.0000   0.0332
 -10.250  -0.9248   0.02852   0.02174  -0.0437   1.0000   0.0343
 -10.000  -0.9006   0.02730   0.02050  -0.0443   1.0000   0.0353
  -9.750  -0.8752   0.02623   0.01936  -0.0448   1.0000   0.0364
  -9.500  -0.8493   0.02518   0.01819  -0.0453   1.0000   0.0378
  -9.250  -0.8227   0.02415   0.01696  -0.0457   1.0000   0.0394
  -9.000  -0.7961   0.02310   0.01586  -0.0462   1.0000   0.0407
  -8.750  -0.7689   0.02224   0.01496  -0.0467   1.0000   0.0422
  -8.500  -0.7411   0.02142   0.01405  -0.0472   1.0000   0.0440
  -8.250  -0.7129   0.02066   0.01313  -0.0476   1.0000   0.0460
  -8.000  -0.6849   0.01979   0.01229  -0.0481   1.0000   0.0479
  -7.750  -0.6563   0.01910   0.01155  -0.0486   1.0000   0.0501
  -7.500  -0.6274   0.01845   0.01080  -0.0491   1.0000   0.0526
  -7.250  -0.5984   0.01772   0.01007  -0.0497   1.0000   0.0553
  -7.000  -0.5692   0.01713   0.00945  -0.0502   1.0000   0.0584
  -6.750  -0.5396   0.01658   0.00883  -0.0506   1.0000   0.0618
  -6.500  -0.5101   0.01597   0.00824  -0.0513   1.0000   0.0660
  -6.000  -0.4503   0.01495   0.00722  -0.0524   1.0000   0.0770
  -5.750  -0.4203   0.01448   0.00677  -0.0529   1.0000   0.0846
  -5.500  -0.3902   0.01406   0.00638  -0.0535   1.0000   0.0945
  -5.250  -0.3600   0.01366   0.00603  -0.0540   1.0000   0.1070
  -5.000  -0.3298   0.01331   0.00572  -0.0546   1.0000   0.1209
  -4.750  -0.2955   0.01305   0.00549  -0.0560   0.9589   0.1360
  -4.500  -0.2635   0.01287   0.00531  -0.0567   0.9225   0.1508
  -4.000  -0.2089   0.01265   0.00502  -0.0557   0.8639   0.1806
  -3.750  -0.1821   0.01254   0.00486  -0.0551   0.8388   0.1956
  -3.500  -0.1546   0.01242   0.00471  -0.0547   0.8148   0.2113
  -3.250  -0.1270   0.01231   0.00457  -0.0544   0.7919   0.2287
  -3.000  -0.0989   0.01222   0.00445  -0.0541   0.7709   0.2483
  -2.750  -0.0703   0.01213   0.00434  -0.0540   0.7509   0.2700
  -2.500  -0.0415   0.01207   0.00424  -0.0539   0.7315   0.2904
  -2.250  -0.0125   0.01202   0.00414  -0.0539   0.7119   0.3086
  -2.000   0.0165   0.01198   0.00406  -0.0539   0.6929   0.3262
  -1.750   0.0457   0.01195   0.00398  -0.0539   0.6746   0.3429
  -1.500   0.0750   0.01193   0.00392  -0.0539   0.6567   0.3602
  -1.250   0.1043   0.01192   0.00387  -0.0539   0.6400   0.3776
  -1.000   0.1337   0.01191   0.00383  -0.0540   0.6247   0.3940
  -0.750   0.1631   0.01191   0.00380  -0.0541   0.6101   0.4107
  -0.500   0.1926   0.01191   0.00379  -0.0542   0.5963   0.4288
  -0.250   0.2222   0.01190   0.00381  -0.0543   0.5832   0.4490
   0.000   0.2516   0.01190   0.00383  -0.0544   0.5707   0.4687
   0.250   0.2810   0.01192   0.00385  -0.0545   0.5581   0.4884
   0.500   0.3104   0.01193   0.00388  -0.0546   0.5451   0.5094
   0.750   0.3399   0.01194   0.00393  -0.0547   0.5326   0.5307
   1.000   0.3692   0.01196   0.00398  -0.0548   0.5206   0.5524
   1.250   0.3982   0.01198   0.00404  -0.0548   0.5082   0.5786
   1.500   0.4271   0.01197   0.00412  -0.0547   0.4950   0.6117
   1.750   0.4557   0.01194   0.00421  -0.0546   0.4814   0.6525
   2.000   0.4836   0.01190   0.00430  -0.0543   0.4678   0.7014
   2.250   0.5099   0.01182   0.00439  -0.0536   0.4548   0.7620
   2.500   0.5321   0.01163   0.00438  -0.0518   0.4427   0.8556
   2.750   0.5586   0.01147   0.00428  -0.0511   0.4299   1.0000
   3.000   0.5884   0.01166   0.00441  -0.0513   0.4174   1.0000
   3.250   0.6180   0.01186   0.00453  -0.0516   0.4048   1.0000
   3.500   0.6475   0.01206   0.00468  -0.0518   0.3920   1.0000
   3.750   0.6770   0.01227   0.00485  -0.0520   0.3789   1.0000
   4.000   0.7063   0.01248   0.00502  -0.0522   0.3660   1.0000
   4.250   0.7355   0.01272   0.00521  -0.0523   0.3528   1.0000
   4.500   0.7646   0.01297   0.00542  -0.0525   0.3395   1.0000
   5.000   0.8223   0.01351   0.00588  -0.0528   0.3100   1.0000
   5.250   0.8510   0.01381   0.00614  -0.0529   0.2933   1.0000
   5.500   0.8794   0.01415   0.00641  -0.0531   0.2753   1.0000
   5.750   0.9076   0.01451   0.00672  -0.0532   0.2569   1.0000
   6.000   0.9357   0.01488   0.00705  -0.0533   0.2374   1.0000
   6.250   0.9635   0.01530   0.00740  -0.0534   0.2173   1.0000
   6.500   0.9910   0.01578   0.00779  -0.0535   0.1984   1.0000
   6.750   1.0183   0.01627   0.00823  -0.0535   0.1807   1.0000
   7.000   1.0453   0.01679   0.00870  -0.0536   0.1643   1.0000
   7.250   1.0720   0.01734   0.00922  -0.0536   0.1487   1.0000
   7.500   1.0984   0.01792   0.00976  -0.0536   0.1339   1.0000
   7.750   1.1245   0.01854   0.01033  -0.0535   0.1190   1.0000
   8.000   1.1501   0.01920   0.01096  -0.0534   0.1050   1.0000
   8.250   1.1752   0.01991   0.01163  -0.0533   0.0922   1.0000
   8.500   1.1998   0.02066   0.01236  -0.0531   0.0813   1.0000
   8.750   1.2239   0.02145   0.01315  -0.0529   0.0726   1.0000
   9.000   1.2473   0.02229   0.01399  -0.0526   0.0657   1.0000
   9.250   1.2700   0.02317   0.01488  -0.0522   0.0601   1.0000
   9.500   1.2924   0.02404   0.01581  -0.0517   0.0558   1.0000
   9.750   1.3136   0.02500   0.01681  -0.0512   0.0522   1.0000
  10.000   1.3340   0.02599   0.01787  -0.0506   0.0492   1.0000
  10.250   1.3538   0.02698   0.01894  -0.0499   0.0465   1.0000
  10.500   1.3711   0.02816   0.02016  -0.0490   0.0444   1.0000
  10.750   1.3877   0.02933   0.02143  -0.0481   0.0426   1.0000
  11.000   1.4034   0.03051   0.02271  -0.0470   0.0409   1.0000
  11.250   1.4169   0.03179   0.02407  -0.0458   0.0394   1.0000
  11.500   1.4260   0.03329   0.02564  -0.0444   0.0381   1.0000
  11.750   1.4312   0.03493   0.02737  -0.0425   0.0372   1.0000
  12.000   1.4346   0.03667   0.02926  -0.0408   0.0363   1.0000
  12.250   1.4375   0.03878   0.03149  -0.0398   0.0354   1.0000
  12.500   1.4399   0.04119   0.03403  -0.0394   0.0347   1.0000
  12.750   1.4418   0.04387   0.03682  -0.0394   0.0340   1.0000
  13.000   1.4426   0.04682   0.03988  -0.0398   0.0334   1.0000
  13.250   1.4420   0.05008   0.04322  -0.0404   0.0328   1.0000
  13.500   1.4395   0.05361   0.04683  -0.0411   0.0323   1.0000
  13.750   1.4380   0.05714   0.05049  -0.0419   0.0318   1.0000
  14.000   1.4360   0.06079   0.05430  -0.0428   0.0313   1.0000
  14.250   1.4328   0.06466   0.05832  -0.0439   0.0307   1.0000
  14.500   1.4286   0.06871   0.06251  -0.0451   0.0302   1.0000
  14.750   1.4234   0.07293   0.06686  -0.0464   0.0298   1.0000
  15.000   1.4175   0.07730   0.07135  -0.0478   0.0293   1.0000
  15.250   1.4109   0.08179   0.07595  -0.0494   0.0290   1.0000
  15.500   1.4041   0.08637   0.08064  -0.0510   0.0286   1.0000
  15.750   1.3977   0.09106   0.08543  -0.0528   0.0283   1.0000
  16.000   1.3916   0.09577   0.09023  -0.0546   0.0280   1.0000
  16.250   1.3859   0.10044   0.09498  -0.0564   0.0277   1.0000
  16.500   1.3813   0.10493   0.09954  -0.0581   0.0275   1.0000
  16.750   1.3728   0.11043   0.10518  -0.0606   0.0272   1.0000
  17.000   1.3623   0.11648   0.11142  -0.0636   0.0270   1.0000
  17.250   1.3508   0.12291   0.11803  -0.0670   0.0268   1.0000
  17.500   1.3382   0.12977   0.12507  -0.0708   0.0265   1.0000
  17.750   1.3239   0.13722   0.13270  -0.0752   0.0263   1.0000
  18.000   1.3071   0.14549   0.14116  -0.0802   0.0261   1.0000
  18.250   1.2863   0.15515   0.15103  -0.0865   0.0259   1.0000
  18.500   1.2499   0.16967   0.16582  -0.0964   0.0259   1.0000
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