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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 500,000
Max Cl/Cd: 116.77 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf095-il-500000.txt
Download as CSV file: xf-oaf095-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4925   0.13255   0.13015  -0.0062   1.0000   0.0278
 -11.750  -0.7994   0.05594   0.05317  -0.0511   1.0000   0.0182
 -11.500  -0.8192   0.04293   0.03986  -0.0691   1.0000   0.0181
 -11.250  -0.7971   0.03455   0.03121  -0.0858   1.0000   0.0185
 -11.000  -0.7702   0.03109   0.02753  -0.0928   1.0000   0.0191
 -10.750  -0.7444   0.02863   0.02486  -0.0971   1.0000   0.0198
 -10.500  -0.7180   0.02649   0.02249  -0.1003   1.0000   0.0207
 -10.250  -0.6912   0.02485   0.02058  -0.1026   1.0000   0.0213
 -10.000  -0.6661   0.02198   0.01747  -0.1054   1.0000   0.0223
  -9.750  -0.6420   0.02095   0.01639  -0.1061   1.0000   0.0231
  -9.500  -0.6197   0.02012   0.01548  -0.1061   1.0000   0.0240
  -9.250  -0.5987   0.01929   0.01453  -0.1059   1.0000   0.0250
  -9.000  -0.5645   0.01851   0.01357  -0.1079   0.9982   0.0262
  -8.750  -0.5284   0.01690   0.01184  -0.1110   0.9964   0.0280
  -8.500  -0.4918   0.01622   0.01111  -0.1135   0.9946   0.0296
  -8.250  -0.4554   0.01551   0.01029  -0.1157   0.9926   0.0314
  -8.000  -0.4192   0.01454   0.00919  -0.1181   0.9902   0.0334
  -7.750  -0.3831   0.01383   0.00845  -0.1204   0.9874   0.0358
  -7.500  -0.3469   0.01330   0.00785  -0.1224   0.9846   0.0382
  -7.250  -0.3116   0.01258   0.00702  -0.1243   0.9810   0.0409
  -7.000  -0.2784   0.01206   0.00649  -0.1257   0.9757   0.0444
  -6.750  -0.2456   0.01174   0.00609  -0.1267   0.9708   0.0476
  -6.500  -0.2156   0.01115   0.00548  -0.1274   0.9637   0.0524
  -6.250  -0.1872   0.01092   0.00519  -0.1274   0.9570   0.0570
  -6.000  -0.1589   0.01051   0.00478  -0.1275   0.9494   0.0638
  -5.750  -0.1318   0.01026   0.00447  -0.1272   0.9425   0.0711
  -5.500  -0.1039   0.01002   0.00423  -0.1271   0.9351   0.0807
  -5.250  -0.0765   0.00975   0.00397  -0.1269   0.9282   0.0926
  -5.000  -0.0482   0.00952   0.00375  -0.1269   0.9211   0.1050
  -4.750  -0.0204   0.00932   0.00355  -0.1268   0.9139   0.1180
  -4.500   0.0077   0.00915   0.00339  -0.1267   0.9067   0.1312
  -4.250   0.0358   0.00900   0.00325  -0.1266   0.8989   0.1452
  -4.000   0.0641   0.00888   0.00311  -0.1265   0.8920   0.1588
  -3.750   0.0929   0.00875   0.00298  -0.1265   0.8845   0.1724
  -3.500   0.1213   0.00865   0.00287  -0.1264   0.8780   0.1860
  -3.250   0.1505   0.00853   0.00276  -0.1266   0.8702   0.1998
  -2.750   0.2084   0.00835   0.00259  -0.1267   0.8558   0.2283
  -2.500   0.2371   0.00828   0.00251  -0.1266   0.8490   0.2431
  -2.250   0.2666   0.00820   0.00246  -0.1268   0.8413   0.2588
  -2.000   0.2955   0.00813   0.00240  -0.1269   0.8341   0.2744
  -1.750   0.3249   0.00807   0.00237  -0.1270   0.8261   0.2914
  -1.500   0.3538   0.00802   0.00233  -0.1271   0.8185   0.3081
  -1.250   0.3832   0.00798   0.00232  -0.1272   0.8103   0.3244
  -1.000   0.4122   0.00796   0.00231  -0.1272   0.8028   0.3415
  -0.750   0.4415   0.00793   0.00232  -0.1274   0.7945   0.3580
  -0.500   0.4705   0.00793   0.00232  -0.1274   0.7868   0.3748
  -0.250   0.4997   0.00791   0.00234  -0.1275   0.7773   0.3919
   0.000   0.5286   0.00792   0.00235  -0.1275   0.7681   0.4086
   0.250   0.5577   0.00791   0.00237  -0.1276   0.7581   0.4248
   0.500   0.5869   0.00791   0.00241  -0.1277   0.7490   0.4411
   0.750   0.6157   0.00794   0.00244  -0.1277   0.7398   0.4587
   1.000   0.6449   0.00793   0.00249  -0.1278   0.7284   0.4767
   1.250   0.6737   0.00794   0.00252  -0.1278   0.7153   0.4957
   1.500   0.7025   0.00795   0.00257  -0.1278   0.7017   0.5168
   2.000   0.7602   0.00798   0.00271  -0.1279   0.6747   0.5744
   2.500   0.8174   0.00783   0.00293  -0.1279   0.6417   0.7130
   2.750   0.8362   0.00735   0.00291  -0.1255   0.6252   1.0000
   3.000   0.8648   0.00751   0.00299  -0.1254   0.6056   1.0000
   3.250   0.8930   0.00770   0.00309  -0.1254   0.5848   1.0000
   3.500   0.9213   0.00789   0.00322  -0.1253   0.5605   1.0000
   3.750   0.9491   0.00814   0.00336  -0.1252   0.5314   1.0000
   4.000   0.9764   0.00847   0.00354  -0.1251   0.4958   1.0000
   4.250   1.0030   0.00890   0.00377  -0.1249   0.4491   1.0000
   4.500   1.0281   0.00960   0.00411  -0.1246   0.3728   1.0000
   4.750   1.0517   0.01058   0.00462  -0.1242   0.2845   1.0000
   5.000   1.0752   0.01153   0.00515  -0.1238   0.2113   1.0000
   5.250   1.0991   0.01236   0.00568  -0.1233   0.1562   1.0000
   5.500   1.1231   0.01313   0.00620  -0.1229   0.1141   1.0000
   5.750   1.1474   0.01382   0.00671  -0.1224   0.0865   1.0000
   6.000   1.1720   0.01443   0.00723  -0.1219   0.0698   1.0000
   6.250   1.1965   0.01501   0.00777  -0.1213   0.0592   1.0000
   6.500   1.2203   0.01566   0.00838  -0.1207   0.0517   1.0000
   6.750   1.2447   0.01620   0.00891  -0.1201   0.0467   1.0000
   7.000   1.2675   0.01693   0.00966  -0.1193   0.0423   1.0000
   7.250   1.2915   0.01743   0.01019  -0.1186   0.0391   1.0000
   7.500   1.3126   0.01829   0.01103  -0.1176   0.0358   1.0000
   7.750   1.3345   0.01899   0.01180  -0.1166   0.0339   1.0000
   8.000   1.3568   0.01961   0.01247  -0.1157   0.0321   1.0000
   8.250   1.3782   0.02028   0.01316  -0.1147   0.0303   1.0000
   8.500   1.3930   0.02168   0.01458  -0.1128   0.0283   1.0000
   8.750   1.4145   0.02225   0.01523  -0.1118   0.0274   1.0000
   9.000   1.4338   0.02303   0.01609  -0.1104   0.0263   1.0000
   9.250   1.4523   0.02384   0.01695  -0.1090   0.0252   1.0000
   9.500   1.4694   0.02472   0.01786  -0.1075   0.0243   1.0000
   9.750   1.4824   0.02597   0.01915  -0.1054   0.0234   1.0000
  10.000   1.4920   0.02759   0.02086  -0.1028   0.0225   1.0000
  10.250   1.5069   0.02840   0.02176  -0.1009   0.0220   1.0000
  10.500   1.5180   0.02937   0.02284  -0.0984   0.0213   1.0000
  10.750   1.5283   0.03049   0.02406  -0.0960   0.0207   1.0000
  11.000   1.5382   0.03169   0.02534  -0.0938   0.0202   1.0000
  11.250   1.5477   0.03296   0.02669  -0.0917   0.0197   1.0000
  11.500   1.5562   0.03436   0.02815  -0.0896   0.0192   1.0000
  11.750   1.5628   0.03608   0.02994  -0.0875   0.0188   1.0000
  12.000   1.5645   0.03897   0.03295  -0.0848   0.0182   1.0000
  12.250   1.5703   0.04073   0.03488  -0.0829   0.0179   1.0000
  12.500   1.5756   0.04253   0.03683  -0.0811   0.0176   1.0000
  12.750   1.5799   0.04447   0.03893  -0.0794   0.0173   1.0000
  13.000   1.5828   0.04663   0.04125  -0.0778   0.0169   1.0000
  13.250   1.5844   0.04899   0.04375  -0.0764   0.0166   1.0000
  13.500   1.5849   0.05155   0.04645  -0.0752   0.0162   1.0000
  13.750   1.5837   0.05435   0.04939  -0.0741   0.0160   1.0000
  14.000   1.5814   0.05734   0.05252  -0.0732   0.0158   1.0000
  14.250   1.5782   0.06056   0.05588  -0.0726   0.0155   1.0000
  14.500   1.5739   0.06396   0.05941  -0.0723   0.0153   1.0000
  14.750   1.5683   0.06765   0.06323  -0.0722   0.0152   1.0000
  15.000   1.5611   0.07168   0.06739  -0.0723   0.0150   1.0000
  15.250   1.5518   0.07615   0.07199  -0.0728   0.0149   1.0000
  15.500   1.5397   0.08127   0.07726  -0.0737   0.0147   1.0000
  15.750   1.5244   0.08715   0.08331  -0.0752   0.0146   1.0000
  16.000   1.5065   0.09376   0.09012  -0.0774   0.0146   1.0000
  16.250   1.4860   0.10118   0.09774  -0.0804   0.0145   1.0000
  16.500   1.4643   0.10930   0.10607  -0.0844   0.0145   1.0000
  16.750   1.4438   0.11772   0.11468  -0.0890   0.0145   1.0000
  17.000   1.4226   0.12680   0.12396  -0.0945   0.0145   1.0000
  17.250   1.4012   0.13661   0.13397  -0.1009   0.0145   1.0000
  17.500   1.3772   0.14797   0.14554  -0.1088   0.0146   1.0000
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