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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 500,000
Max Cl/Cd: 75.71 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63145-il-500000.txt
Download as CSV file: xf-fx63145-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0951   0.08677   0.08248  -0.0815   0.4953   0.0177
 -10.500  -0.0890   0.08418   0.07984  -0.0819   0.4846   0.0182
 -10.250  -0.0860   0.08070   0.07632  -0.0829   0.4766   0.0186
 -10.000  -0.0847   0.07682   0.07242  -0.0842   0.4689   0.0191
  -9.750  -0.0845   0.07264   0.06824  -0.0856   0.4630   0.0196
  -9.500  -0.0881   0.06734   0.06298  -0.0878   0.4677   0.0205
  -9.250  -0.0930   0.06179   0.05747  -0.0903   0.4670   0.0207
  -9.000  -0.1093   0.05221   0.04793  -0.0961   0.4705   0.0210
  -8.750  -0.1188   0.04673   0.04243  -0.0993   0.4648   0.0207
  -8.500  -0.1360   0.04095   0.03663  -0.1033   0.4679   0.0202
  -8.250  -0.1587   0.03622   0.03187  -0.1065   0.4736   0.0203
  -8.000  -0.1803   0.03320   0.02876  -0.1075   0.4690   0.0202
  -7.750  -0.1900   0.02966   0.02501  -0.1093   0.4678   0.0206
  -7.500  -0.2026   0.02478   0.01958  -0.1108   0.4667   0.0219
  -7.250  -0.1859   0.02258   0.01744  -0.1110   0.4601   0.0226
  -7.000  -0.1706   0.02099   0.01569  -0.1111   0.4258   0.0236
  -6.750  -0.1580   0.01822   0.01231  -0.1118   0.4101   0.0272
  -6.500  -0.1388   0.01679   0.01077  -0.1118   0.3644   0.0280
  -6.250  -0.1149   0.01722   0.01047  -0.1115   0.3411   0.0321
  -6.000  -0.0963   0.01376   0.00696  -0.1125   0.3040   0.0332
  -5.750  -0.0737   0.01255   0.00562  -0.1127   0.2861   0.0345
  -5.500  -0.0444   0.01300   0.00553  -0.1125   0.2750   0.0384
  -5.250  -0.0229   0.02306   0.01511  -0.1187   0.2365   0.0401
  -5.000   0.0035   0.02187   0.01378  -0.1188   0.2269   0.0425
  -4.500   0.0621   0.01732   0.00851  -0.1157   0.2158   0.0173
  -4.250   0.0885   0.01613   0.00734  -0.1154   0.2105   0.0156
  -4.000   0.1164   0.01537   0.00645  -0.1154   0.1867   0.0143
  -3.750   0.1449   0.01499   0.00592  -0.1155   0.1798   0.0135
  -3.500   0.1739   0.01471   0.00556  -0.1158   0.1759   0.0131
  -3.250   0.2038   0.01428   0.00507  -0.1164   0.1737   0.0130
  -3.000   0.2341   0.01385   0.00459  -0.1171   0.1713   0.0129
  -2.750   0.2642   0.01357   0.00423  -0.1176   0.1688   0.0130
  -2.500   0.2942   0.01334   0.00391  -0.1181   0.1662   0.0133
  -2.250   0.3240   0.01317   0.00366  -0.1185   0.1642   0.0142
  -2.000   0.3536   0.01307   0.00348  -0.1188   0.1613   0.0164
  -1.750   0.3824   0.01307   0.00342  -0.1190   0.1380   0.0384
  -1.500   0.4118   0.01297   0.00332  -0.1194   0.1323   0.0528
  -1.250   0.4407   0.01295   0.00330  -0.1197   0.1304   0.0928
  -1.000   0.4689   0.01302   0.00333  -0.1198   0.1294   0.0991
  -0.750   0.4975   0.01305   0.00332  -0.1199   0.1282   0.1054
  -0.500   0.5262   0.01306   0.00334  -0.1202   0.1273   0.1153
  -0.250   0.5548   0.01309   0.00338  -0.1204   0.1264   0.1404
   0.000   0.5831   0.01315   0.00342  -0.1205   0.1256   0.1512
   0.250   0.6131   0.01300   0.00346  -0.1212   0.1249   0.2113
   0.500   0.6422   0.01298   0.00351  -0.1217   0.1241   0.2608
   0.750   0.6707   0.01301   0.00359  -0.1219   0.1234   0.2743
   1.000   0.6991   0.01306   0.00368  -0.1221   0.1228   0.3046
   1.250   0.7271   0.01315   0.00378  -0.1222   0.1220   0.3152
   1.500   0.7560   0.01314   0.00389  -0.1226   0.1212   0.3557
   1.750   0.7844   0.01318   0.00401  -0.1228   0.1202   0.3869
   2.000   0.8132   0.01319   0.00416  -0.1232   0.1190   0.4407
   2.250   0.8417   0.01323   0.00434  -0.1235   0.1167   0.4918
   2.750   0.8971   0.01345   0.00472  -0.1237   0.1134   0.5512
   3.000   0.9245   0.01358   0.00491  -0.1237   0.1118   0.5715
   3.250   0.9522   0.01367   0.00508  -0.1237   0.1057   0.5888
   3.500   0.9787   0.01388   0.00530  -0.1235   0.1045   0.6045
   3.750   1.0049   0.01410   0.00553  -0.1233   0.1033   0.6207
   4.000   1.0310   0.01433   0.00579  -0.1231   0.1017   0.6368
   4.250   1.0570   0.01455   0.00603  -0.1229   0.1004   0.6481
   4.500   1.0830   0.01477   0.00626  -0.1227   0.0992   0.6541
   4.750   1.1088   0.01498   0.00651  -0.1224   0.0983   0.6604
   5.250   1.1598   0.01546   0.00704  -0.1218   0.0971   0.6737
   5.500   1.1849   0.01572   0.00734  -0.1215   0.0967   0.6807
   5.750   1.2098   0.01598   0.00764  -0.1211   0.0964   0.6868
   6.000   1.2333   0.01634   0.00804  -0.1205   0.0952   0.6944
   6.250   1.2546   0.01688   0.00859  -0.1196   0.0925   0.7020
   6.500   1.2770   0.01728   0.00905  -0.1189   0.0908   0.7097
   6.750   1.3000   0.01763   0.00945  -0.1183   0.0900   0.7173
   7.000   1.3227   0.01796   0.00986  -0.1176   0.0894   0.7254
   7.500   1.3594   0.01918   0.01125  -0.1150   0.0843   0.7449
   7.750   1.3768   0.01978   0.01191  -0.1136   0.0816   0.7554
   8.000   1.4030   0.01979   0.01199  -0.1134   0.0788   0.7677
   8.250   1.4257   0.01997   0.01227  -0.1127   0.0746   0.7829
   8.500   1.4485   0.02011   0.01251  -0.1120   0.0605   0.8044
   8.750   1.4619   0.02058   0.01291  -0.1098   0.0566   0.8323
   9.000   1.4710   0.02100   0.01349  -0.1067   0.0536   0.8805
   9.250   1.4748   0.02148   0.01412  -0.1027   0.0512   1.0000
   9.500   1.4835   0.02242   0.01512  -0.1002   0.0480   1.0000
   9.750   1.4947   0.02325   0.01599  -0.0982   0.0457   1.0000
  10.000   1.5095   0.02390   0.01669  -0.0968   0.0435   1.0000
  10.250   1.5209   0.02476   0.01761  -0.0951   0.0351   1.0000
  10.500   1.5192   0.02652   0.01928  -0.0922   0.0230   1.0000
  10.750   1.5240   0.02801   0.02078  -0.0904   0.0187   1.0000
  11.000   1.5294   0.02958   0.02240  -0.0889   0.0161   1.0000
  11.250   1.5341   0.03133   0.02422  -0.0876   0.0142   1.0000
  11.500   1.5401   0.03312   0.02608  -0.0866   0.0129   1.0000
  11.750   1.5420   0.03540   0.02843  -0.0858   0.0100   1.0000
  12.000   1.5415   0.03808   0.03115  -0.0851   0.0054   1.0000
  12.250   1.5401   0.04099   0.03413  -0.0846   0.0041   1.0000
  12.500   1.5389   0.04401   0.03723  -0.0844   0.0038   1.0000
  12.750   1.5383   0.04705   0.04038  -0.0843   0.0036   1.0000
  13.000   1.5375   0.05020   0.04363  -0.0843   0.0034   1.0000
  13.250   1.5371   0.05335   0.04690  -0.0844   0.0033   1.0000
  13.500   1.5363   0.05665   0.05030  -0.0847   0.0032   1.0000
  13.750   1.5346   0.06014   0.05391  -0.0851   0.0032   1.0000
  14.000   1.5324   0.06376   0.05765  -0.0856   0.0031   1.0000
  14.250   1.5296   0.06760   0.06160  -0.0862   0.0030   1.0000
  14.500   1.5262   0.07162   0.06575  -0.0870   0.0030   1.0000
  14.750   1.5221   0.07589   0.07014  -0.0880   0.0029   1.0000
  15.000   1.5166   0.08047   0.07485  -0.0892   0.0029   1.0000
  15.250   1.5111   0.08516   0.07967  -0.0906   0.0028   1.0000
  15.500   1.5055   0.09001   0.08465  -0.0921   0.0028   1.0000
  15.750   1.4986   0.09517   0.08994  -0.0938   0.0028   1.0000
  16.000   1.4913   0.10053   0.09544  -0.0957   0.0028   1.0000
  16.250   1.4838   0.10601   0.10105  -0.0978   0.0028   1.0000
  16.500   1.4762   0.11160   0.10677  -0.1000   0.0027   1.0000
  16.750   1.4673   0.11753   0.11283  -0.1026   0.0027   1.0000
  17.000   1.4591   0.12343   0.11885  -0.1052   0.0027   1.0000
  17.250   1.4503   0.12951   0.12506  -0.1081   0.0027   1.0000
  17.500   1.4419   0.13553   0.13121  -0.1110   0.0027   1.0000
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