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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 50,000
Max Cl/Cd: 43.89 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf095-il-50000.txt
Download as CSV file: xf-oaf095-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF095 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4173   0.12422   0.11687  -0.0171   1.0000   0.2121
  -9.500  -0.3912   0.11805   0.11064  -0.0158   1.0000   0.2219
  -9.250  -0.4090   0.11872   0.11144  -0.0189   1.0000   0.2269
  -9.000  -0.3794   0.11164   0.10429  -0.0173   1.0000   0.2342
  -8.750  -0.3881   0.11084   0.10359  -0.0193   1.0000   0.2416
  -8.500  -0.3713   0.10576   0.09850  -0.0190   1.0000   0.2471
  -8.250  -0.3746   0.10431   0.09714  -0.0200   1.0000   0.2567
  -8.000  -0.3588   0.09982   0.09263  -0.0195   1.0000   0.2649
  -7.750  -0.3747   0.09970   0.09268  -0.0205   1.0000   0.2731
  -7.500  -0.3517   0.09433   0.08726  -0.0197   1.0000   0.2807
  -7.250  -0.3715   0.09440   0.08751  -0.0193   1.0000   0.2886
  -7.000  -0.3510   0.08953   0.08261  -0.0182   1.0000   0.2968
  -6.750  -0.3750   0.08984   0.08313  -0.0173   1.0000   0.3045
  -6.500  -0.3595   0.08574   0.07903  -0.0147   1.0000   0.3157
  -6.250  -0.3759   0.08470   0.07815  -0.0139   1.0000   0.3226
  -6.000  -0.3708   0.08203   0.07551  -0.0113   1.0000   0.3331
  -5.750  -0.3790   0.08005   0.07363  -0.0105   1.0000   0.3395
  -5.500  -0.3602   0.05891   0.05201  -0.0553   1.0000   0.1959
  -5.250  -0.3570   0.05967   0.05292  -0.0473   1.0000   0.2063
  -5.000  -0.3228   0.05152   0.04445  -0.0596   1.0000   0.2036
  -4.750  -0.2581   0.04042   0.03236  -0.0800   1.0000   0.2122
  -4.500  -0.2376   0.03910   0.03104  -0.0794   1.0000   0.2228
  -4.250  -0.1963   0.03545   0.02682  -0.0858   1.0000   0.2429
  -4.000  -0.1704   0.03413   0.02540  -0.0865   1.0000   0.2595
  -3.750  -0.1462   0.03325   0.02446  -0.0866   1.0000   0.2773
  -3.500  -0.1211   0.03244   0.02358  -0.0869   1.0000   0.2971
  -3.250  -0.0875   0.03113   0.02194  -0.0895   1.0000   0.3216
  -3.000  -0.0644   0.03071   0.02155  -0.0891   1.0000   0.3409
  -2.750  -0.0377   0.03015   0.02090  -0.0897   1.0000   0.3626
  -2.500  -0.0085   0.02952   0.02011  -0.0911   1.0000   0.3864
  -2.250   0.0153   0.02922   0.01982  -0.0910   1.0000   0.4074
  -2.000   0.0445   0.02883   0.01927  -0.0924   1.0000   0.4327
  -1.750   0.0677   0.02867   0.01916  -0.0922   1.0000   0.4543
  -1.500   0.0953   0.02848   0.01888  -0.0933   1.0000   0.4803
  -1.250   0.1192   0.02840   0.01884  -0.0935   1.0000   0.5041
  -1.000   0.1448   0.02837   0.01880  -0.0941   1.0000   0.5309
  -0.750   0.1710   0.02839   0.01881  -0.0949   1.0000   0.5591
  -0.500   0.1963   0.02850   0.01892  -0.0955   1.0000   0.5891
  -0.250   0.2211   0.02866   0.01910  -0.0960   1.0000   0.6200
   0.000   0.2448   0.02884   0.01936  -0.0963   1.0000   0.6534
   0.250   0.2682   0.02905   0.01968  -0.0965   1.0000   0.6915
   0.500   0.2908   0.02925   0.02006  -0.0965   1.0000   0.7378
   0.750   0.3101   0.02930   0.02040  -0.0957   1.0000   0.8021
   1.000   0.3092   0.02913   0.02057  -0.0922   0.9982   1.0000
   1.250   0.3748   0.03044   0.02144  -0.1027   0.9873   1.0000
   1.500   0.4238   0.03164   0.02239  -0.1087   0.9759   1.0000
   1.750   0.4670   0.03280   0.02341  -0.1131   0.9640   1.0000
   2.000   0.5087   0.03396   0.02449  -0.1171   0.9520   1.0000
   2.250   0.5520   0.03511   0.02561  -0.1211   0.9399   1.0000
   2.500   0.5912   0.03621   0.02671  -0.1243   0.9269   1.0000
   2.750   0.6237   0.03730   0.02782  -0.1262   0.9128   1.0000
   3.000   0.6571   0.03836   0.02896  -0.1281   0.8981   1.0000
   3.250   0.6917   0.03936   0.03003  -0.1300   0.8827   1.0000
   3.500   0.7287   0.04024   0.03102  -0.1319   0.8663   1.0000
   3.750   0.7701   0.04088   0.03182  -0.1340   0.8490   1.0000
   4.000   0.8022   0.04154   0.03261  -0.1345   0.8295   1.0000
   4.250   0.8356   0.04196   0.03320  -0.1348   0.8082   1.0000
   4.500   0.8898   0.04121   0.03273  -0.1365   0.7871   1.0000
   4.750   0.9255   0.04078   0.03252  -0.1356   0.7621   1.0000
   5.000   0.9853   0.03782   0.02989  -0.1345   0.7378   1.0000
   5.250   1.0327   0.03461   0.02695  -0.1310   0.7096   1.0000
   5.500   1.0747   0.03123   0.02381  -0.1265   0.6774   1.0000
   5.750   1.1026   0.02900   0.02175  -0.1214   0.6354   1.0000
   6.000   1.1270   0.02684   0.01963  -0.1157   0.5754   1.0000
   6.250   1.1389   0.02595   0.01819  -0.1087   0.4553   1.0000
   6.500   1.1390   0.02837   0.01912  -0.1029   0.3165   1.0000
   6.750   1.1511   0.03127   0.02111  -0.1002   0.2487   1.0000
   7.000   1.1732   0.03372   0.02323  -0.0987   0.2088   1.0000
   7.250   1.2011   0.03616   0.02544  -0.0979   0.1835   1.0000
   7.500   1.2286   0.03859   0.02784  -0.0973   0.1655   1.0000
   7.750   1.2560   0.04129   0.03062  -0.0967   0.1530   1.0000
   8.000   1.2820   0.04416   0.03347  -0.0962   0.1429   1.0000
   8.250   1.3028   0.04722   0.03704  -0.0948   0.1366   1.0000
   8.500   1.3274   0.05066   0.04038  -0.0945   0.1297   1.0000
   8.750   1.3380   0.05409   0.04455  -0.0921   0.1262   1.0000
   9.000   1.3480   0.05818   0.04922  -0.0901   0.1244   1.0000
   9.250   1.3536   0.06241   0.05395  -0.0879   0.1229   1.0000
   9.500   1.3556   0.06667   0.05864  -0.0857   0.1212   1.0000
   9.750   1.3549   0.07100   0.06333  -0.0835   0.1197   1.0000
  10.000   1.3440   0.07588   0.06863  -0.0811   0.1197   1.0000
  10.250   1.3192   0.08134   0.07453  -0.0784   0.1214   1.0000
  10.500   1.2856   0.08674   0.08024  -0.0759   0.1236   1.0000
  10.750   1.2534   0.09259   0.08628  -0.0750   0.1256   1.0000
  11.000   1.2262   0.09917   0.09300  -0.0757   0.1274   1.0000
  11.250   1.2077   0.10606   0.09997  -0.0772   0.1289   1.0000
  11.500   1.1213   0.12616   0.12020  -0.0922   0.1455   1.0000
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