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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.9 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63158-il-1000000-n5.txt
Download as CSV file: xf-fx63158-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0636   0.07969   0.07582  -0.1076   0.4915   0.0077
  -8.250  -0.2748   0.02530   0.01985  -0.1238   0.4915   0.0043
  -8.000  -0.2642   0.02265   0.01686  -0.1225   0.4802   0.0042
  -7.750  -0.2474   0.02064   0.01458  -0.1217   0.4758   0.0042
  -7.500  -0.2281   0.01897   0.01265  -0.1209   0.4673   0.0042
  -7.250  -0.2068   0.01782   0.01130  -0.1202   0.4590   0.0042
  -7.000  -0.1854   0.01703   0.01028  -0.1195   0.4271   0.0042
  -6.750  -0.1630   0.01630   0.00936  -0.1189   0.4107   0.0042
  -6.500  -0.1396   0.01568   0.00860  -0.1185   0.3965   0.0042
  -6.250  -0.1169   0.01526   0.00796  -0.1179   0.3584   0.0043
  -6.000  -0.0926   0.01486   0.00742  -0.1177   0.3397   0.0043
  -5.750  -0.0688   0.01462   0.00699  -0.1173   0.2976   0.0043
  -5.250  -0.0192   0.01355   0.00552  -0.1176   0.2239   0.0048
  -5.000   0.0077   0.01335   0.00516  -0.1179   0.1822   0.0050
  -4.750   0.0362   0.01310   0.00484  -0.1184   0.1734   0.0052
  -4.500   0.0653   0.01286   0.00455  -0.1190   0.1680   0.0055
  -4.250   0.0944   0.01268   0.00431  -0.1196   0.1586   0.0058
  -4.000   0.1231   0.01258   0.00410  -0.1201   0.1345   0.0060
  -3.750   0.1524   0.01246   0.00391  -0.1206   0.1286   0.0062
  -3.500   0.1819   0.01234   0.00375  -0.1212   0.1254   0.0064
  -3.250   0.2114   0.01225   0.00362  -0.1218   0.1222   0.0065
  -3.000   0.2407   0.01219   0.00351  -0.1223   0.1158   0.0068
  -2.750   0.2703   0.01212   0.00340  -0.1228   0.1122   0.0076
  -2.500   0.2990   0.01213   0.00334  -0.1232   0.0929   0.0080
  -2.000   0.3574   0.01210   0.00327  -0.1241   0.0874   0.0095
  -1.750   0.3864   0.01211   0.00325  -0.1245   0.0864   0.0141
  -1.500   0.4153   0.01213   0.00324  -0.1249   0.0854   0.0157
  -1.250   0.4441   0.01215   0.00324  -0.1252   0.0845   0.0175
  -1.000   0.4731   0.01217   0.00325  -0.1256   0.0836   0.0209
  -0.750   0.5018   0.01221   0.00329  -0.1260   0.0827   0.0330
  -0.500   0.5302   0.01227   0.00333  -0.1263   0.0820   0.0349
  -0.250   0.5588   0.01231   0.00336  -0.1266   0.0813   0.0378
   0.000   0.5873   0.01236   0.00339  -0.1269   0.0808   0.0412
   0.250   0.6157   0.01243   0.00345  -0.1272   0.0803   0.0426
   0.500   0.6439   0.01249   0.00351  -0.1274   0.0800   0.0441
   0.750   0.6723   0.01256   0.00357  -0.1277   0.0798   0.0461
   1.000   0.7020   0.01255   0.00365  -0.1284   0.0797   0.0988
   1.250   0.7304   0.01260   0.00373  -0.1287   0.0795   0.1130
   1.500   0.7589   0.01266   0.00382  -0.1291   0.0790   0.1369
   1.750   0.7868   0.01275   0.00392  -0.1293   0.0786   0.1429
   2.000   0.8147   0.01284   0.00402  -0.1295   0.0781   0.1511
   2.250   0.8434   0.01290   0.00413  -0.1300   0.0774   0.1760
   2.500   0.8712   0.01299   0.00424  -0.1302   0.0740   0.1966
   2.750   0.8989   0.01314   0.00441  -0.1306   0.0601   0.2411
   3.250   0.9583   0.01319   0.00472  -0.1322   0.0568   0.3673
   3.500   0.9935   0.01299   0.00488  -0.1346   0.0563   0.5142
   3.750   1.0231   0.01304   0.00513  -0.1353   0.0558   0.5886
   4.000   1.0494   0.01324   0.00538  -0.1353   0.0554   0.6152
   4.250   1.0751   0.01345   0.00562  -0.1350   0.0549   0.6281
   4.500   1.1004   0.01368   0.00586  -0.1348   0.0545   0.6343
   4.750   1.1254   0.01391   0.00609  -0.1344   0.0541   0.6363
   5.000   1.1503   0.01415   0.00635  -0.1341   0.0537   0.6400
   5.250   1.1748   0.01440   0.00664  -0.1337   0.0533   0.6447
   5.500   1.1988   0.01466   0.00692  -0.1332   0.0527   0.6485
   5.750   1.2222   0.01496   0.00723  -0.1326   0.0517   0.6514
   6.000   1.2452   0.01526   0.00754  -0.1319   0.0509   0.6533
   6.250   1.2686   0.01552   0.00782  -0.1313   0.0508   0.6546
   6.500   1.2916   0.01579   0.00812  -0.1307   0.0506   0.6559
   6.750   1.3143   0.01605   0.00842  -0.1300   0.0501   0.6574
   7.000   1.3366   0.01632   0.00872  -0.1293   0.0490   0.6590
   7.250   1.3573   0.01660   0.00904  -0.1282   0.0475   0.6605
   7.500   1.3761   0.01691   0.00938  -0.1268   0.0461   0.6620
   7.750   1.3939   0.01728   0.00977  -0.1252   0.0444   0.6635
   8.000   1.4122   0.01762   0.01014  -0.1238   0.0434   0.6650
   8.250   1.4310   0.01795   0.01050  -0.1225   0.0418   0.6666
   8.750   1.4589   0.01906   0.01154  -0.1184   0.0272   0.6696
   9.000   1.4711   0.01972   0.01220  -0.1162   0.0241   0.6710
   9.250   1.4855   0.02029   0.01282  -0.1144   0.0226   0.6727
   9.500   1.4972   0.02101   0.01357  -0.1123   0.0191   0.6745
   9.750   1.5030   0.02206   0.01462  -0.1095   0.0139   0.6765
  10.000   1.5119   0.02300   0.01559  -0.1073   0.0120   0.6787
  10.250   1.5200   0.02405   0.01668  -0.1051   0.0104   0.6811
  10.500   1.5291   0.02509   0.01777  -0.1033   0.0094   0.6836
  10.750   1.5343   0.02645   0.01917  -0.1012   0.0068   0.6858
  11.000   1.5324   0.02845   0.02119  -0.0987   0.0024   0.6874
  11.250   1.5379   0.03004   0.02286  -0.0971   0.0022   0.6896
  11.500   1.5433   0.03176   0.02466  -0.0958   0.0020   0.6920
  11.750   1.5480   0.03363   0.02662  -0.0946   0.0019   0.6937
  12.000   1.5524   0.03564   0.02872  -0.0936   0.0018   0.6957
  12.250   1.5565   0.03778   0.03094  -0.0928   0.0017   0.6975
  12.500   1.5601   0.04005   0.03329  -0.0921   0.0016   0.6992
  12.750   1.5634   0.04243   0.03575  -0.0915   0.0015   0.7008
  13.000   1.5668   0.04487   0.03828  -0.0911   0.0015   0.7024
  13.250   1.5697   0.04744   0.04092  -0.0908   0.0015   0.7037
  13.500   1.5719   0.05013   0.04370  -0.0905   0.0014   0.7049
  13.750   1.5737   0.05295   0.04661  -0.0904   0.0014   0.7065
  14.000   1.5751   0.05590   0.04965  -0.0904   0.0014   0.7079
  14.250   1.5763   0.05892   0.05277  -0.0905   0.0013   0.7092
  14.500   1.5771   0.06207   0.05601  -0.0906   0.0013   0.7104
  14.750   1.5776   0.06533   0.05937  -0.0909   0.0012   0.7115
  15.000   1.5776   0.06876   0.06288  -0.0913   0.0012   0.7127
  15.250   1.5776   0.07223   0.06645  -0.0918   0.0011   0.7138
  15.500   1.5777   0.07575   0.07006  -0.0924   0.0011   0.7150
  15.750   1.5768   0.07951   0.07391  -0.0931   0.0011   0.7161
  16.000   1.5755   0.08339   0.07790  -0.0940   0.0010   0.7173
  16.250   1.5750   0.08721   0.08180  -0.0949   0.0010   0.7184
  16.500   1.5724   0.09140   0.08610  -0.0960   0.0010   0.7195
  16.750   1.5703   0.09558   0.09037  -0.0971   0.0009   0.7205
  17.000   1.5681   0.09982   0.09471  -0.0984   0.0009   0.7215
  17.500   1.5608   0.10901   0.10411  -0.1015   0.0009   0.7237
  17.750   1.5560   0.11384   0.10906  -0.1032   0.0008   0.7249
  18.000   1.5510   0.11880   0.11412  -0.1052   0.0008   0.7262
  18.250   1.5460   0.12377   0.11922  -0.1072   0.0008   0.7275
  18.500   1.5389   0.12918   0.12474  -0.1096   0.0008   0.7288
  18.750   1.5339   0.13421   0.12988  -0.1120   0.0008   0.7302
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