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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 100,000
Max Cl/Cd: 49.45 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf117-il-100000-n5.txt
Download as CSV file: xf-oaf117-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7028   0.10383   0.09854   0.0109   1.0000   0.0463
 -11.000  -0.8126   0.07316   0.06774  -0.0111   1.0000   0.0454
 -10.750  -0.8620   0.05879   0.05310  -0.0264   1.0000   0.0446
 -10.500  -0.8806   0.05004   0.04380  -0.0364   1.0000   0.0450
 -10.250  -0.8817   0.04409   0.03715  -0.0410   1.0000   0.0461
 -10.000  -0.8629   0.04224   0.03531  -0.0415   1.0000   0.0472
  -9.750  -0.8442   0.04004   0.03295  -0.0426   1.0000   0.0485
  -9.500  -0.8248   0.03749   0.03011  -0.0437   1.0000   0.0501
  -9.250  -0.8038   0.03492   0.02711  -0.0450   1.0000   0.0522
  -9.000  -0.7807   0.03288   0.02483  -0.0458   1.0000   0.0542
  -8.750  -0.7560   0.03149   0.02340  -0.0463   1.0000   0.0561
  -8.500  -0.7307   0.02991   0.02164  -0.0469   1.0000   0.0583
  -8.250  -0.7043   0.02831   0.01969  -0.0475   1.0000   0.0612
  -8.000  -0.6782   0.02707   0.01848  -0.0480   1.0000   0.0637
  -7.750  -0.6512   0.02592   0.01726  -0.0485   1.0000   0.0666
  -7.500  -0.6234   0.02475   0.01587  -0.0489   1.0000   0.0703
  -7.250  -0.5959   0.02373   0.01488  -0.0494   1.0000   0.0739
  -7.000  -0.5677   0.02279   0.01387  -0.0499   1.0000   0.0783
  -6.750  -0.5393   0.02186   0.01288  -0.0504   1.0000   0.0832
  -6.500  -0.5105   0.02108   0.01208  -0.0509   1.0000   0.0892
  -6.250  -0.4816   0.02029   0.01128  -0.0515   1.0000   0.0959
  -6.000  -0.4523   0.01961   0.01054  -0.0520   1.0000   0.1049
  -5.750  -0.4230   0.01893   0.00990  -0.0526   1.0000   0.1151
  -5.500  -0.3935   0.01830   0.00929  -0.0532   1.0000   0.1278
  -5.250  -0.3639   0.01772   0.00875  -0.0538   1.0000   0.1422
  -5.000  -0.3342   0.01723   0.00831  -0.0544   1.0000   0.1582
  -4.750  -0.3045   0.01682   0.00790  -0.0549   1.0000   0.1758
  -4.500  -0.2748   0.01643   0.00754  -0.0555   1.0000   0.1934
  -4.250  -0.2453   0.01605   0.00726  -0.0560   1.0000   0.2109
  -4.000  -0.2159   0.01574   0.00704  -0.0566   1.0000   0.2296
  -3.750  -0.1849   0.01549   0.00687  -0.0575   0.9887   0.2502
  -3.500  -0.1456   0.01532   0.00671  -0.0598   0.9531   0.2749
  -3.250  -0.1101   0.01518   0.00660  -0.0612   0.9224   0.2966
  -3.000  -0.0795   0.01510   0.00651  -0.0613   0.8931   0.3168
  -2.750  -0.0518   0.01505   0.00643  -0.0608   0.8655   0.3356
  -2.500  -0.0251   0.01501   0.00634  -0.0600   0.8405   0.3544
  -2.250   0.0018   0.01497   0.00625  -0.0593   0.8168   0.3731
  -2.000   0.0287   0.01493   0.00617  -0.0586   0.7947   0.3916
  -1.750   0.0558   0.01490   0.00608  -0.0580   0.7739   0.4105
  -1.500   0.0834   0.01488   0.00602  -0.0575   0.7545   0.4297
  -1.250   0.1111   0.01484   0.00597  -0.0571   0.7359   0.4494
  -1.000   0.1388   0.01482   0.00593  -0.0566   0.7172   0.4712
  -0.750   0.1667   0.01480   0.00590  -0.0562   0.6983   0.4942
  -0.500   0.1948   0.01479   0.00586  -0.0558   0.6801   0.5167
  -0.250   0.2227   0.01477   0.00584  -0.0555   0.6633   0.5375
   0.000   0.2509   0.01476   0.00583  -0.0551   0.6477   0.5603
   0.250   0.2791   0.01475   0.00584  -0.0549   0.6323   0.5869
   0.500   0.3070   0.01472   0.00588  -0.0545   0.6176   0.6178
   0.750   0.3346   0.01469   0.00594  -0.0540   0.6039   0.6544
   1.000   0.3612   0.01463   0.00598  -0.0533   0.5910   0.6969
   1.250   0.3861   0.01454   0.00601  -0.0521   0.5783   0.7500
   1.750   0.4345   0.01407   0.00583  -0.0492   0.5516   1.0000
   2.000   0.4646   0.01428   0.00591  -0.0495   0.5384   1.0000
   2.250   0.4944   0.01451   0.00601  -0.0497   0.5251   1.0000
   2.500   0.5241   0.01472   0.00614  -0.0500   0.5107   1.0000
   2.750   0.5537   0.01495   0.00629  -0.0502   0.4961   1.0000
   3.000   0.5831   0.01518   0.00646  -0.0504   0.4816   1.0000
   3.250   0.6123   0.01542   0.00663  -0.0505   0.4675   1.0000
   3.500   0.6414   0.01567   0.00682  -0.0506   0.4539   1.0000
   3.750   0.6703   0.01594   0.00702  -0.0507   0.4405   1.0000
   4.000   0.6993   0.01621   0.00727  -0.0508   0.4263   1.0000
   4.250   0.7282   0.01649   0.00754  -0.0509   0.4121   1.0000
   4.500   0.7569   0.01678   0.00783  -0.0510   0.3980   1.0000
   4.750   0.7854   0.01709   0.00812  -0.0510   0.3837   1.0000
   5.000   0.8137   0.01741   0.00842  -0.0510   0.3695   1.0000
   5.250   0.8418   0.01775   0.00876  -0.0510   0.3545   1.0000
   5.500   0.8698   0.01811   0.00910  -0.0510   0.3391   1.0000
   5.750   0.8975   0.01849   0.00949  -0.0510   0.3226   1.0000
   6.000   0.9251   0.01889   0.00989  -0.0510   0.3049   1.0000
   6.250   0.9523   0.01931   0.01031  -0.0510   0.2862   1.0000
   6.500   0.9790   0.01980   0.01077  -0.0509   0.2670   1.0000
   6.750   1.0054   0.02033   0.01128  -0.0508   0.2476   1.0000
   7.000   1.0316   0.02090   0.01183  -0.0508   0.2276   1.0000
   7.250   1.0574   0.02151   0.01244  -0.0507   0.2078   1.0000
   7.500   1.0825   0.02221   0.01310  -0.0506   0.1889   1.0000
   7.750   1.1068   0.02301   0.01385  -0.0504   0.1712   1.0000
   8.000   1.1305   0.02389   0.01468  -0.0502   0.1545   1.0000
   8.250   1.1538   0.02479   0.01561  -0.0499   0.1386   1.0000
   8.500   1.1763   0.02577   0.01660  -0.0495   0.1238   1.0000
   8.750   1.1977   0.02684   0.01767  -0.0491   0.1109   1.0000
   9.000   1.2179   0.02802   0.01884  -0.0486   0.1001   1.0000
   9.250   1.2375   0.02921   0.02008  -0.0480   0.0908   1.0000
   9.500   1.2559   0.03048   0.02142  -0.0472   0.0835   1.0000
   9.750   1.2716   0.03193   0.02283  -0.0464   0.0779   1.0000
  10.000   1.2881   0.03326   0.02433  -0.0454   0.0727   1.0000
  10.250   1.3012   0.03480   0.02589  -0.0443   0.0689   1.0000
  10.500   1.3135   0.03638   0.02758  -0.0431   0.0655   1.0000
  10.750   1.3243   0.03799   0.02930  -0.0418   0.0624   1.0000
  11.000   1.3316   0.03975   0.03111  -0.0404   0.0601   1.0000
  11.250   1.3350   0.04167   0.03309  -0.0386   0.0584   1.0000
  11.500   1.3389   0.04369   0.03530  -0.0372   0.0565   1.0000
  11.750   1.3421   0.04595   0.03770  -0.0362   0.0547   1.0000
  12.000   1.3444   0.04841   0.04026  -0.0357   0.0532   1.0000
  12.250   1.3462   0.05103   0.04294  -0.0355   0.0519   1.0000
  12.500   1.3480   0.05381   0.04576  -0.0353   0.0507   1.0000
  12.750   1.3485   0.05695   0.04915  -0.0355   0.0495   1.0000
  13.000   1.3481   0.06027   0.05266  -0.0358   0.0484   1.0000
  13.250   1.3465   0.06379   0.05635  -0.0364   0.0475   1.0000
  13.500   1.3440   0.06750   0.06021  -0.0372   0.0466   1.0000
  13.750   1.3409   0.07131   0.06414  -0.0382   0.0457   1.0000
  14.000   1.3382   0.07509   0.06801  -0.0392   0.0450   1.0000
  14.250   1.3368   0.07866   0.07163  -0.0400   0.0442   1.0000
  14.500   1.3306   0.08313   0.07623  -0.0414   0.0436   1.0000
  14.750   1.3161   0.08919   0.08256  -0.0442   0.0431   1.0000
  15.000   1.2990   0.09586   0.08949  -0.0475   0.0427   1.0000
  15.250   1.2795   0.10326   0.09714  -0.0515   0.0424   1.0000
  15.500   1.2566   0.11183   0.10595  -0.0565   0.0422   1.0000
  15.750   1.2269   0.12249   0.11688  -0.0632   0.0421   1.0000
  16.000   1.1775   0.13905   0.13375  -0.0742   0.0424   1.0000
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