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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.92 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63145-il-1000000.txt
Download as CSV file: xf-fx63145-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1558   0.06517   0.06033  -0.1021   0.1420   0.0089
  -9.000  -0.1813   0.05476   0.04993  -0.1104   0.1617   0.0087
  -8.750  -0.2070   0.04890   0.04401  -0.1142   0.1605   0.0082
  -8.500  -0.2296   0.04560   0.04067  -0.1145   0.1625   0.0082
  -8.250  -0.2369   0.04243   0.03738  -0.1161   0.1625   0.0086
  -7.750  -0.2438   0.03281   0.02701  -0.1170   0.1616   0.0101
  -7.500  -0.2266   0.03141   0.02551  -0.1171   0.1337   0.0103
  -7.250  -0.2075   0.03011   0.02410  -0.1174   0.1323   0.0106
  -7.000  -0.1869   0.02878   0.02264  -0.1177   0.1299   0.0110
  -6.750  -0.1644   0.02728   0.02091  -0.1178   0.1277   0.0122
  -6.500  -0.1424   0.02451   0.01768  -0.1182   0.1259   0.0136
  -6.250  -0.1178   0.02349   0.01664  -0.1185   0.1242   0.0141
  -6.000  -0.0921   0.02252   0.01554  -0.1189   0.1236   0.0149
  -5.750  -0.0627   0.02314   0.01592  -0.1187   0.1222   0.0169
  -5.500  -0.0381   0.01992   0.01249  -0.1194   0.1211   0.0181
  -5.250  -0.0112   0.01908   0.01158  -0.1196   0.1185   0.0190
  -5.000   0.0174   0.01887   0.01121  -0.1197   0.1157   0.0211
  -4.750   0.0443   0.01743   0.00967  -0.1200   0.1140   0.0237
  -4.500   0.0724   0.01688   0.00900  -0.1203   0.1120   0.0281
  -3.750   0.1579   0.01356   0.00535  -0.1189   0.0933   0.0121
  -2.750   0.2791   0.01208   0.00358  -0.1211   0.0900   0.0090
  -2.500   0.3090   0.01193   0.00336  -0.1215   0.0898   0.0088
  -2.250   0.3384   0.01184   0.00321  -0.1218   0.0896   0.0087
  -2.000   0.3677   0.01178   0.00311  -0.1220   0.0894   0.0088
  -1.750   0.3968   0.01176   0.00304  -0.1222   0.0892   0.0092
  -1.500   0.4258   0.01175   0.00301  -0.1224   0.0890   0.0111
  -1.250   0.4548   0.01173   0.00301  -0.1226   0.0888   0.0316
  -1.000   0.4833   0.01178   0.00303  -0.1227   0.0886   0.0348
  -0.750   0.5117   0.01184   0.00308  -0.1228   0.0884   0.0383
  -0.500   0.5401   0.01189   0.00311  -0.1229   0.0882   0.0410
  -0.250   0.5686   0.01194   0.00315  -0.1231   0.0880   0.0447
   0.000   0.5969   0.01199   0.00321  -0.1232   0.0877   0.0514
   0.250   0.6250   0.01207   0.00330  -0.1233   0.0875   0.0632
   0.500   0.6531   0.01216   0.00338  -0.1234   0.0873   0.0714
   0.750   0.6812   0.01224   0.00351  -0.1235   0.0870   0.0977
   1.000   0.7092   0.01233   0.00360  -0.1236   0.0868   0.1042
   1.250   0.7368   0.01246   0.00372  -0.1236   0.0865   0.1054
   1.500   0.7641   0.01261   0.00387  -0.1235   0.0860   0.1063
   1.750   0.7913   0.01276   0.00402  -0.1234   0.0854   0.1071
   2.000   0.8184   0.01293   0.00419  -0.1234   0.0850   0.1079
   2.250   0.8453   0.01310   0.00438  -0.1232   0.0845   0.1097
   2.500   0.8721   0.01328   0.00457  -0.1231   0.0841   0.1125
   2.750   0.8988   0.01348   0.00480  -0.1230   0.0835   0.1163
   3.000   0.9251   0.01369   0.00507  -0.1229   0.0829   0.1359
   3.250   0.9508   0.01397   0.00538  -0.1226   0.0823   0.1412
   3.500   0.9781   0.01407   0.00550  -0.1226   0.0821   0.1477
   3.750   1.0055   0.01416   0.00559  -0.1226   0.0818   0.1520
   4.000   1.0329   0.01425   0.00572  -0.1226   0.0814   0.1598
   4.250   1.0604   0.01434   0.00586  -0.1227   0.0810   0.1917
   4.500   1.0872   0.01447   0.00600  -0.1227   0.0805   0.1992
   4.750   1.1148   0.01454   0.00618  -0.1228   0.0799   0.2413
   5.000   1.1419   0.01465   0.00636  -0.1229   0.0795   0.2704
   5.250   1.1694   0.01472   0.00650  -0.1231   0.0784   0.3156
   5.500   1.1981   0.01469   0.00660  -0.1235   0.0765   0.3789
   5.750   1.2264   0.01470   0.00678  -0.1240   0.0754   0.4561
   6.000   1.2548   0.01470   0.00695  -0.1244   0.0743   0.5333
   6.250   1.2821   0.01475   0.00708  -0.1245   0.0722   0.5675
   6.500   1.3066   0.01504   0.00727  -0.1241   0.0585   0.5818
   6.750   1.3308   0.01533   0.00760  -0.1237   0.0541   0.5963
   7.000   1.3547   0.01565   0.00800  -0.1231   0.0526   0.6124
   7.250   1.3771   0.01606   0.00848  -0.1224   0.0500   0.6237
   7.500   1.3986   0.01651   0.00897  -0.1215   0.0464   0.6314
   7.750   1.4229   0.01674   0.00923  -0.1211   0.0447   0.6385
   8.000   1.4416   0.01734   0.00975  -0.1198   0.0261   0.6459
   8.250   1.4548   0.01827   0.01061  -0.1177   0.0096   0.6529
   8.500   1.4708   0.01895   0.01129  -0.1160   0.0034   0.6621
   8.750   1.4895   0.01940   0.01180  -0.1147   0.0028   0.6719
   9.000   1.5045   0.01989   0.01234  -0.1127   0.0027   0.6822
   9.250   1.5185   0.02041   0.01295  -0.1106   0.0026   0.6917
   9.500   1.5316   0.02099   0.01360  -0.1085   0.0026   0.7015
   9.750   1.5434   0.02165   0.01435  -0.1062   0.0025   0.7131
  10.000   1.5536   0.02241   0.01522  -0.1039   0.0024   0.7273
  10.250   1.5623   0.02330   0.01621  -0.1015   0.0023   0.7438
  10.500   1.5701   0.02428   0.01731  -0.0991   0.0022   0.7615
  10.750   1.5772   0.02536   0.01854  -0.0970   0.0022   0.7929
  11.000   1.5822   0.02656   0.01995  -0.0948   0.0021   0.8483
  11.250   1.5795   0.02775   0.02141  -0.0914   0.0021   1.0000
  11.500   1.5828   0.02950   0.02324  -0.0897   0.0021   1.0000
  11.750   1.5850   0.03149   0.02533  -0.0884   0.0020   1.0000
  12.000   1.5856   0.03383   0.02775  -0.0873   0.0020   1.0000
  12.250   1.5849   0.03644   0.03047  -0.0865   0.0020   1.0000
  12.500   1.5818   0.03949   0.03363  -0.0859   0.0019   1.0000
  12.750   1.5805   0.04250   0.03673  -0.0856   0.0019   1.0000
  13.000   1.5808   0.04542   0.03974  -0.0854   0.0019   1.0000
  13.250   1.5795   0.04862   0.04303  -0.0854   0.0018   1.0000
  13.500   1.5766   0.05209   0.04660  -0.0856   0.0018   1.0000
  13.750   1.5729   0.05574   0.05035  -0.0859   0.0018   1.0000
  14.000   1.5678   0.05972   0.05443  -0.0864   0.0018   1.0000
  14.250   1.5617   0.06394   0.05876  -0.0871   0.0017   1.0000
  14.500   1.5551   0.06839   0.06332  -0.0879   0.0017   1.0000
  14.750   1.5475   0.07317   0.06821  -0.0891   0.0017   1.0000
  15.000   1.5387   0.07828   0.07344  -0.0904   0.0016   1.0000
  15.250   1.5308   0.08338   0.07866  -0.0919   0.0016   1.0000
  15.500   1.5223   0.08876   0.08414  -0.0936   0.0016   1.0000
  15.750   1.5122   0.09454   0.09004  -0.0956   0.0016   1.0000
  16.000   1.5024   0.10042   0.09604  -0.0978   0.0015   1.0000
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