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OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: OAF095 AIRFOIL (oaf095-il)
Reynolds number: 100,000
Max Cl/Cd: 63.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf095-il-100000-n5.txt
Download as CSV file: xf-oaf095-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4703   0.08778   0.08257  -0.0347   1.0000   0.0407
  -9.250  -0.4629   0.08543   0.08025  -0.0358   1.0000   0.0420
  -9.000  -0.5688   0.04633   0.04087  -0.0785   1.0000   0.0392
  -8.750  -0.5567   0.04072   0.03493  -0.0860   1.0000   0.0405
  -8.500  -0.5390   0.03859   0.03271  -0.0879   1.0000   0.0421
  -8.250  -0.5187   0.03506   0.02879  -0.0918   1.0000   0.0441
  -8.000  -0.4951   0.03143   0.02460  -0.0954   1.0000   0.0461
  -7.750  -0.4704   0.02880   0.02153  -0.0976   1.0000   0.0487
  -7.500  -0.4486   0.02777   0.02049  -0.0979   1.0000   0.0512
  -7.250  -0.4245   0.02634   0.01884  -0.0987   1.0000   0.0543
  -7.000  -0.3987   0.02476   0.01685  -0.0996   1.0000   0.0576
  -6.750  -0.3681   0.02373   0.01582  -0.1013   0.9978   0.0617
  -6.500  -0.3300   0.02254   0.01438  -0.1042   0.9941   0.0673
  -6.250  -0.2933   0.02154   0.01329  -0.1069   0.9897   0.0733
  -6.000  -0.2552   0.02064   0.01215  -0.1095   0.9857   0.0814
  -5.750  -0.2171   0.01987   0.01136  -0.1122   0.9821   0.0906
  -5.500  -0.1805   0.01919   0.01060  -0.1145   0.9771   0.1012
  -5.250  -0.1421   0.01860   0.00995  -0.1171   0.9731   0.1144
  -5.000  -0.1029   0.01811   0.00940  -0.1198   0.9696   0.1295
  -4.750  -0.0678   0.01773   0.00897  -0.1216   0.9636   0.1453
  -4.500  -0.0303   0.01738   0.00855  -0.1237   0.9589   0.1629
  -4.250   0.0057   0.01708   0.00819  -0.1256   0.9536   0.1804
  -4.000   0.0397   0.01683   0.00792  -0.1270   0.9470   0.1973
  -3.750   0.0762   0.01657   0.00767  -0.1288   0.9422   0.2148
  -3.500   0.1077   0.01640   0.00749  -0.1296   0.9345   0.2310
  -3.250   0.1418   0.01621   0.00728  -0.1308   0.9284   0.2481
  -3.000   0.1731   0.01607   0.00714  -0.1314   0.9209   0.2645
  -2.750   0.2051   0.01593   0.00701  -0.1321   0.9138   0.2816
  -2.500   0.2358   0.01582   0.00690  -0.1326   0.9063   0.2990
  -2.250   0.2661   0.01572   0.00681  -0.1329   0.8985   0.3168
  -2.000   0.2960   0.01565   0.00674  -0.1331   0.8908   0.3354
  -1.750   0.3254   0.01557   0.00668  -0.1332   0.8826   0.3537
  -1.500   0.3543   0.01551   0.00666  -0.1332   0.8746   0.3716
  -1.250   0.3833   0.01545   0.00663  -0.1331   0.8667   0.3895
  -1.000   0.4118   0.01541   0.00663  -0.1330   0.8585   0.4076
  -0.750   0.4404   0.01535   0.00661  -0.1329   0.8507   0.4256
  -0.500   0.4685   0.01533   0.00664  -0.1327   0.8424   0.4440
   0.000   0.5248   0.01527   0.00670  -0.1323   0.8264   0.4831
   0.250   0.5529   0.01523   0.00673  -0.1320   0.8187   0.5049
   0.500   0.5805   0.01523   0.00682  -0.1317   0.8098   0.5286
   0.750   0.6084   0.01516   0.00685  -0.1313   0.8025   0.5558
   1.000   0.6356   0.01515   0.00698  -0.1310   0.7930   0.5864
   1.250   0.6628   0.01502   0.00701  -0.1303   0.7853   0.6240
   1.500   0.6883   0.01492   0.00715  -0.1295   0.7747   0.6766
   1.750   0.7091   0.01461   0.00719  -0.1273   0.7649   0.7800
   2.000   0.7312   0.01436   0.00709  -0.1254   0.7556   1.0000
   2.250   0.7595   0.01453   0.00724  -0.1253   0.7443   1.0000
   2.500   0.7878   0.01465   0.00735  -0.1251   0.7331   1.0000
   2.750   0.8156   0.01474   0.00743  -0.1246   0.7199   1.0000
   3.000   0.8429   0.01482   0.00749  -0.1240   0.7040   1.0000
   3.250   0.8700   0.01491   0.00757  -0.1234   0.6863   1.0000
   3.500   0.8969   0.01501   0.00766  -0.1227   0.6673   1.0000
   3.750   0.9236   0.01511   0.00773  -0.1219   0.6466   1.0000
   4.000   0.9496   0.01527   0.00788  -0.1211   0.6208   1.0000
   4.250   0.9754   0.01545   0.00802  -0.1202   0.5918   1.0000
   4.500   1.0006   0.01570   0.00820  -0.1193   0.5576   1.0000
   4.750   1.0251   0.01603   0.00842  -0.1183   0.5154   1.0000
   5.000   1.0482   0.01652   0.00869  -0.1171   0.4606   1.0000
   5.250   1.0689   0.01732   0.00912  -0.1158   0.3808   1.0000
   5.500   1.0864   0.01858   0.00982  -0.1143   0.2913   1.0000
   5.750   1.1037   0.01997   0.01073  -0.1130   0.2166   1.0000
   6.000   1.1221   0.02125   0.01169  -0.1118   0.1643   1.0000
   6.250   1.1408   0.02248   0.01269  -0.1106   0.1293   1.0000
   6.500   1.1600   0.02359   0.01370  -0.1094   0.1066   1.0000
   6.750   1.1787   0.02472   0.01476  -0.1082   0.0915   1.0000
   7.000   1.1972   0.02583   0.01587  -0.1068   0.0810   1.0000
   7.250   1.2145   0.02703   0.01705  -0.1054   0.0731   1.0000
   7.500   1.2321   0.02816   0.01825  -0.1039   0.0666   1.0000
   7.750   1.2477   0.02948   0.01959  -0.1023   0.0620   1.0000
   8.000   1.2647   0.03066   0.02087  -0.1007   0.0573   1.0000
   8.250   1.2795   0.03201   0.02221  -0.0991   0.0537   1.0000
   8.750   1.3116   0.03483   0.02528  -0.0958   0.0481   1.0000
   9.000   1.3266   0.03620   0.02670  -0.0942   0.0454   1.0000
   9.250   1.3403   0.03791   0.02835  -0.0926   0.0433   1.0000
   9.500   1.3573   0.03952   0.03021  -0.0911   0.0415   1.0000
   9.750   1.3735   0.04131   0.03219  -0.0896   0.0398   1.0000
  10.000   1.3875   0.04304   0.03410  -0.0880   0.0382   1.0000
  10.250   1.3981   0.04466   0.03581  -0.0860   0.0367   1.0000
  10.500   1.4088   0.04655   0.03771  -0.0843   0.0354   1.0000
  10.750   1.4180   0.04882   0.04026  -0.0823   0.0343   1.0000
  11.000   1.4252   0.05136   0.04313  -0.0802   0.0334   1.0000
  11.250   1.4292   0.05408   0.04615  -0.0780   0.0326   1.0000
  11.500   1.4298   0.05691   0.04930  -0.0758   0.0319   1.0000
  11.750   1.4276   0.05981   0.05246  -0.0738   0.0312   1.0000
  12.000   1.4235   0.06279   0.05568  -0.0720   0.0305   1.0000
  12.250   1.4183   0.06587   0.05897  -0.0705   0.0300   1.0000
  12.500   1.4124   0.06908   0.06237  -0.0694   0.0294   1.0000
  12.750   1.4059   0.07252   0.06596  -0.0686   0.0290   1.0000
  13.000   1.3990   0.07620   0.06977  -0.0682   0.0285   1.0000
  13.250   1.3853   0.08096   0.07473  -0.0682   0.0283   1.0000
  13.500   1.3643   0.08682   0.08092  -0.0693   0.0282   1.0000
  13.750   1.3419   0.09334   0.08773  -0.0714   0.0281   1.0000
  14.000   1.3188   0.10050   0.09516  -0.0744   0.0281   1.0000
  14.250   1.2943   0.10851   0.10342  -0.0786   0.0281   1.0000
  14.500   1.2693   0.11752   0.11264  -0.0840   0.0282   1.0000
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