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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 200,000
Max Cl/Cd: 88.16 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf095-il-200000.txt
Download as CSV file: xf-oaf095-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4102   0.09626   0.09264  -0.0272   1.0000   0.0759
  -8.750  -0.4961   0.06857   0.06515  -0.0482   1.0000   0.0489
  -8.500  -0.5438   0.03838   0.03427  -0.0869   1.0000   0.0442
  -8.250  -0.5234   0.03222   0.02739  -0.0942   1.0000   0.0460
  -8.000  -0.4983   0.02889   0.02337  -0.0976   1.0000   0.0479
  -7.750  -0.4736   0.02526   0.01939  -0.1001   1.0000   0.0498
  -7.500  -0.4512   0.02404   0.01809  -0.1004   1.0000   0.0519
  -7.250  -0.4276   0.02301   0.01687  -0.1007   1.0000   0.0549
  -7.000  -0.4020   0.02196   0.01545  -0.1012   1.0000   0.0577
  -6.750  -0.3749   0.02013   0.01353  -0.1023   1.0000   0.0609
  -6.500  -0.3397   0.01941   0.01269  -0.1044   0.9980   0.0658
  -6.250  -0.2991   0.01811   0.01120  -0.1075   0.9955   0.0714
  -6.000  -0.2590   0.01743   0.01046  -0.1104   0.9927   0.0783
  -5.750  -0.2196   0.01653   0.00952  -0.1132   0.9892   0.0867
  -5.500  -0.1788   0.01580   0.00872  -0.1162   0.9861   0.0975
  -5.250  -0.1368   0.01519   0.00810  -0.1193   0.9836   0.1116
  -5.000  -0.0983   0.01476   0.00767  -0.1218   0.9791   0.1276
  -4.750  -0.0581   0.01442   0.00732  -0.1245   0.9751   0.1457
  -4.500  -0.0157   0.01412   0.00696  -0.1276   0.9722   0.1654
  -4.250   0.0271   0.01373   0.00663  -0.1308   0.9699   0.1847
  -4.000   0.0628   0.01350   0.00643  -0.1325   0.9635   0.2028
  -3.750   0.1025   0.01326   0.00620  -0.1349   0.9593   0.2227
  -3.500   0.1411   0.01308   0.00597  -0.1370   0.9550   0.2424
  -3.250   0.1736   0.01291   0.00586  -0.1379   0.9472   0.2598
  -3.000   0.2090   0.01271   0.00572  -0.1392   0.9420   0.2774
  -2.750   0.2380   0.01263   0.00566  -0.1392   0.9330   0.2940
  -2.500   0.2691   0.01252   0.00558  -0.1395   0.9269   0.3115
  -2.250   0.2967   0.01247   0.00557  -0.1393   0.9177   0.3285
  -2.000   0.3253   0.01239   0.00551  -0.1389   0.9111   0.3468
  -1.750   0.3525   0.01237   0.00552  -0.1386   0.9017   0.3653
  -1.500   0.3800   0.01231   0.00546  -0.1380   0.8952   0.3846
  -1.250   0.4072   0.01228   0.00551  -0.1377   0.8859   0.4030
  -1.000   0.4342   0.01221   0.00549  -0.1370   0.8795   0.4218
  -0.750   0.4617   0.01219   0.00553  -0.1368   0.8698   0.4410
  -0.500   0.4887   0.01212   0.00549  -0.1361   0.8631   0.4603
  -0.250   0.5165   0.01210   0.00553  -0.1359   0.8536   0.4800
   0.000   0.5437   0.01202   0.00552  -0.1353   0.8467   0.4996
   0.250   0.5714   0.01197   0.00556  -0.1351   0.8372   0.5204
   0.500   0.5987   0.01190   0.00556  -0.1346   0.8290   0.5432
   0.750   0.6258   0.01179   0.00556  -0.1340   0.8196   0.5687
   1.000   0.6533   0.01170   0.00561  -0.1336   0.8098   0.5990
   1.250   0.6803   0.01155   0.00559  -0.1329   0.8018   0.6384
   1.500   0.7067   0.01135   0.00569  -0.1323   0.7911   0.7026
   1.750   0.7213   0.01073   0.00553  -0.1285   0.7814   1.0000
   2.000   0.7498   0.01075   0.00544  -0.1281   0.7705   1.0000
   2.250   0.7778   0.01078   0.00541  -0.1277   0.7566   1.0000
   2.500   0.8057   0.01082   0.00540  -0.1273   0.7426   1.0000
   2.750   0.8334   0.01088   0.00543  -0.1269   0.7283   1.0000
   3.000   0.8610   0.01093   0.00544  -0.1263   0.7128   1.0000
   3.250   0.8884   0.01099   0.00544  -0.1258   0.6957   1.0000
   3.500   0.9157   0.01107   0.00548  -0.1252   0.6779   1.0000
   3.750   0.9430   0.01117   0.00557  -0.1247   0.6576   1.0000
   4.000   0.9700   0.01129   0.00566  -0.1242   0.6357   1.0000
   4.250   0.9969   0.01145   0.00578  -0.1236   0.6113   1.0000
   4.500   1.0232   0.01164   0.00592  -0.1230   0.5827   1.0000
   4.750   1.0491   0.01190   0.00609  -0.1223   0.5459   1.0000
   5.000   1.0738   0.01230   0.00631  -0.1215   0.4967   1.0000
   5.250   1.0962   0.01298   0.00667  -0.1205   0.4214   1.0000
   5.500   1.1136   0.01436   0.00735  -0.1190   0.3029   1.0000
   5.750   1.1297   0.01606   0.00837  -0.1177   0.1964   1.0000
   6.000   1.1471   0.01760   0.00944  -0.1164   0.1330   1.0000
   6.250   1.1661   0.01888   0.01050  -0.1152   0.1042   1.0000
   6.500   1.1847   0.02014   0.01163  -0.1138   0.0885   1.0000
   6.750   1.2054   0.02109   0.01258  -0.1126   0.0782   1.0000
   7.000   1.2247   0.02222   0.01373  -0.1112   0.0710   1.0000
   7.250   1.2427   0.02345   0.01492  -0.1098   0.0651   1.0000
   7.500   1.2622   0.02460   0.01613  -0.1084   0.0604   1.0000
   7.750   1.2818   0.02565   0.01720  -0.1071   0.0565   1.0000
   8.000   1.2990   0.02765   0.01911  -0.1056   0.0530   1.0000
   8.250   1.3202   0.02864   0.02025  -0.1044   0.0506   1.0000
   8.500   1.3405   0.02976   0.02148  -0.1032   0.0478   1.0000
   8.750   1.3603   0.03105   0.02277  -0.1020   0.0455   1.0000
   9.000   1.3838   0.03394   0.02564  -0.1016   0.0433   1.0000
   9.250   1.4031   0.03521   0.02716  -0.1001   0.0421   1.0000
   9.500   1.4218   0.03676   0.02895  -0.0987   0.0404   1.0000
   9.750   1.4396   0.03833   0.03068  -0.0973   0.0388   1.0000
  10.000   1.4566   0.04012   0.03261  -0.0960   0.0375   1.0000
  10.250   1.4733   0.04222   0.03482  -0.0947   0.0365   1.0000
  10.500   1.4896   0.04555   0.03831  -0.0936   0.0356   1.0000
  10.750   1.4964   0.04990   0.04301  -0.0915   0.0350   1.0000
  11.000   1.4969   0.05215   0.04567  -0.0882   0.0345   1.0000
  11.250   1.4931   0.05486   0.04875  -0.0847   0.0340   1.0000
  11.500   1.4831   0.05768   0.05190  -0.0807   0.0336   1.0000
  11.750   1.4692   0.06091   0.05543  -0.0768   0.0334   1.0000
  12.000   1.4526   0.06460   0.05941  -0.0736   0.0332   1.0000
  12.250   1.4333   0.06887   0.06397  -0.0713   0.0332   1.0000
  12.500   1.4118   0.07366   0.06903  -0.0697   0.0333   1.0000
  12.750   1.3884   0.07902   0.07464  -0.0692   0.0335   1.0000
  13.000   1.3634   0.08500   0.08086  -0.0697   0.0336   1.0000
  13.250   1.3375   0.09161   0.08769  -0.0714   0.0338   1.0000
  13.500   1.3110   0.09896   0.09524  -0.0742   0.0341   1.0000
  13.750   1.2842   0.10708   0.10353  -0.0781   0.0344   1.0000
  14.000   1.2585   0.11587   0.11245  -0.0829   0.0347   1.0000
  14.250   1.1445   0.15454   0.15152  -0.1091   0.0432   1.0000
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