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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 500,000
Max Cl/Cd: 72.1 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63145-il-500000-n5.txt
Download as CSV file: xf-fx63145-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-145 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1572   0.10100   0.09521  -0.0817   0.1648   0.0111
 -10.750  -0.1536   0.09743   0.09165  -0.0832   0.1646   0.0112
  -7.750  -0.2324   0.04066   0.03456  -0.1134   0.1629   0.0140
  -6.750  -0.1769   0.02682   0.01932  -0.1140   0.1333   0.0093
  -6.500  -0.1544   0.02476   0.01701  -0.1142   0.1302   0.0088
  -6.250  -0.1302   0.02197   0.01373  -0.1139   0.1280   0.0076
  -6.000  -0.1034   0.02118   0.01273  -0.1138   0.1264   0.0072
  -5.750  -0.0766   0.02060   0.01200  -0.1138   0.1246   0.0071
  -5.500  -0.0512   0.01919   0.01047  -0.1137   0.1238   0.0069
  -5.250  -0.0247   0.01825   0.00941  -0.1137   0.1229   0.0068
  -5.000   0.0023   0.01745   0.00852  -0.1137   0.1217   0.0067
  -4.750   0.0297   0.01677   0.00775  -0.1138   0.1206   0.0067
  -4.500   0.0576   0.01617   0.00707  -0.1140   0.1188   0.0066
  -4.250   0.0861   0.01564   0.00646  -0.1144   0.1169   0.0066
  -4.000   0.1150   0.01519   0.00594  -0.1149   0.1147   0.0065
  -3.750   0.1445   0.01478   0.00545  -0.1154   0.1134   0.0065
  -3.500   0.1742   0.01442   0.00503  -0.1159   0.1115   0.0066
  -3.250   0.2037   0.01416   0.00468  -0.1164   0.0976   0.0066
  -3.000   0.2331   0.01396   0.00438  -0.1168   0.0966   0.0067
  -2.750   0.2624   0.01382   0.00415  -0.1172   0.0955   0.0068
  -2.500   0.2916   0.01371   0.00395  -0.1175   0.0937   0.0069
  -2.250   0.3207   0.01363   0.00379  -0.1178   0.0921   0.0071
  -1.750   0.3787   0.01353   0.00357  -0.1183   0.0898   0.0087
  -1.500   0.4076   0.01350   0.00353  -0.1185   0.0891   0.0168
  -1.250   0.4362   0.01351   0.00354  -0.1187   0.0886   0.0354
  -1.000   0.4645   0.01356   0.00355  -0.1188   0.0883   0.0379
  -0.750   0.4928   0.01361   0.00357  -0.1189   0.0880   0.0397
  -0.500   0.5212   0.01364   0.00359  -0.1191   0.0877   0.0441
  -0.250   0.5497   0.01367   0.00362  -0.1193   0.0874   0.0517
   0.000   0.5777   0.01375   0.00370  -0.1193   0.0872   0.0675
   0.250   0.6059   0.01381   0.00379  -0.1195   0.0869   0.0980
   0.500   0.6340   0.01388   0.00385  -0.1196   0.0867   0.1046
   0.750   0.6616   0.01400   0.00395  -0.1196   0.0864   0.1054
   1.000   0.6891   0.01412   0.00407  -0.1196   0.0862   0.1062
   1.250   0.7165   0.01425   0.00419  -0.1196   0.0860   0.1072
   1.500   0.7438   0.01439   0.00432  -0.1195   0.0858   0.1086
   1.750   0.7711   0.01452   0.00447  -0.1195   0.0856   0.1132
   2.000   0.7987   0.01462   0.00463  -0.1196   0.0854   0.1236
   2.250   0.8254   0.01481   0.00481  -0.1195   0.0850   0.1391
   2.500   0.8521   0.01499   0.00501  -0.1194   0.0845   0.1449
   2.750   0.8785   0.01519   0.00521  -0.1192   0.0841   0.1489
   3.000   0.9050   0.01537   0.00542  -0.1191   0.0838   0.1549
   3.250   0.9319   0.01553   0.00567  -0.1191   0.0835   0.1843
   3.500   0.9579   0.01575   0.00591  -0.1189   0.0832   0.1978
   3.750   0.9845   0.01592   0.00616  -0.1189   0.0829   0.2175
   4.000   1.0120   0.01602   0.00645  -0.1193   0.0826   0.3122
   4.250   1.0407   0.01603   0.00679  -0.1200   0.0823   0.4352
   4.500   1.0677   0.01615   0.00706  -0.1201   0.0821   0.4812
   4.750   1.0935   0.01636   0.00732  -0.1199   0.0820   0.5011
   5.250   1.1450   0.01677   0.00790  -0.1196   0.0817   0.5403
   5.500   1.1700   0.01701   0.00819  -0.1192   0.0815   0.5558
   5.750   1.1947   0.01726   0.00849  -0.1188   0.0813   0.5660
   6.000   1.2197   0.01749   0.00878  -0.1185   0.0808   0.5773
   6.250   1.2455   0.01763   0.00898  -0.1183   0.0786   0.5899
   6.500   1.2702   0.01784   0.00926  -0.1180   0.0761   0.6022
   6.750   1.2940   0.01812   0.00959  -0.1175   0.0748   0.6120
   7.000   1.3184   0.01834   0.00985  -0.1170   0.0736   0.6198
   7.250   1.3418   0.01861   0.01017  -0.1165   0.0601   0.6274
   7.500   1.3616   0.01912   0.01056  -0.1154   0.0531   0.6338
   7.750   1.3792   0.01974   0.01126  -0.1140   0.0488   0.6400
   8.000   1.3970   0.02031   0.01188  -0.1126   0.0459   0.6466
   8.250   1.4166   0.02068   0.01233  -0.1115   0.0436   0.6547
   8.500   1.4227   0.02166   0.01322  -0.1083   0.0207   0.6644
   8.750   1.4318   0.02250   0.01407  -0.1056   0.0124   0.6764
   9.000   1.4426   0.02326   0.01489  -0.1034   0.0091   0.6877
   9.250   1.4496   0.02426   0.01594  -0.1007   0.0028   0.6994
   9.500   1.4598   0.02512   0.01692  -0.0986   0.0025   0.7132
   9.750   1.4691   0.02608   0.01802  -0.0966   0.0024   0.7331
  10.000   1.4775   0.02716   0.01922  -0.0947   0.0023   0.7523
  10.250   1.4847   0.02837   0.02059  -0.0929   0.0022   0.7735
  10.500   1.4907   0.02972   0.02211  -0.0912   0.0021   0.8051
  10.750   1.4944   0.03116   0.02377  -0.0893   0.0020   0.8603
  11.000   1.4924   0.03270   0.02551  -0.0867   0.0020   1.0000
  11.250   1.4969   0.03471   0.02762  -0.0859   0.0020   1.0000
  11.500   1.5007   0.03692   0.02993  -0.0852   0.0019   1.0000
  11.750   1.5038   0.03931   0.03241  -0.0848   0.0019   1.0000
  12.000   1.5065   0.04184   0.03505  -0.0845   0.0019   1.0000
  12.250   1.5086   0.04453   0.03783  -0.0843   0.0019   1.0000
  12.500   1.5098   0.04738   0.04078  -0.0842   0.0018   1.0000
  12.750   1.5103   0.05039   0.04390  -0.0843   0.0018   1.0000
  13.000   1.5098   0.05358   0.04720  -0.0845   0.0018   1.0000
  13.250   1.5084   0.05696   0.05068  -0.0848   0.0017   1.0000
  13.500   1.5066   0.06050   0.05433  -0.0852   0.0017   1.0000
  13.750   1.5041   0.06418   0.05813  -0.0857   0.0016   1.0000
  14.000   1.5012   0.06805   0.06212  -0.0864   0.0016   1.0000
  14.250   1.4977   0.07213   0.06631  -0.0873   0.0015   1.0000
  14.500   1.4940   0.07636   0.07065  -0.0883   0.0015   1.0000
  14.750   1.4899   0.08075   0.07516  -0.0895   0.0015   1.0000
  15.000   1.4850   0.08539   0.07992  -0.0909   0.0014   1.0000
  15.250   1.4800   0.09015   0.08480  -0.0924   0.0014   1.0000
  15.500   1.4742   0.09516   0.08993  -0.0941   0.0014   1.0000
  15.750   1.4676   0.10042   0.09532  -0.0960   0.0014   1.0000
  16.000   1.4609   0.10580   0.10082  -0.0980   0.0014   1.0000
  16.250   1.4541   0.11126   0.10641  -0.1002   0.0013   1.0000
  16.500   1.4467   0.11692   0.11219  -0.1026   0.0013   1.0000
  16.750   1.4387   0.12280   0.11819  -0.1052   0.0013   1.0000
  17.000   1.4318   0.12853   0.12403  -0.1079   0.0013   1.0000
  17.250   1.4234   0.13459   0.13021  -0.1109   0.0013   1.0000
  17.500   1.4149   0.14075   0.13649  -0.1140   0.0012   1.0000
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