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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 200,000
Max Cl/Cd: 59.1 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63145-il-200000-n5.txt
Download as CSV file: xf-fx63145-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1005   0.10053   0.09635  -0.0739   0.7525   0.0307
 -11.000  -0.1088   0.09480   0.09055  -0.0784   0.7354   0.0320
 -10.500  -0.1647   0.09886   0.09452  -0.0767   0.7708   0.0298
  -9.000  -0.1776   0.06078   0.05601  -0.1021   0.6736   0.0167
  -8.750  -0.1814   0.05709   0.05225  -0.1045   0.6611   0.0164
  -8.500  -0.1928   0.05281   0.04788  -0.1075   0.6517   0.0161
  -8.250  -0.1701   0.03599   0.03113  -0.1035   0.6258   0.0151
  -7.750  -0.2271   0.03932   0.03338  -0.1126   0.6257   0.0128
  -7.500  -0.2165   0.03680   0.03063  -0.1129   0.6143   0.0126
  -7.250  -0.2028   0.03429   0.02784  -0.1132   0.6055   0.0124
  -7.000  -0.1865   0.03183   0.02506  -0.1134   0.5968   0.0121
  -6.750  -0.1673   0.02944   0.02233  -0.1136   0.5869   0.0118
  -6.500  -0.1459   0.02724   0.01976  -0.1136   0.5767   0.0115
  -6.250  -0.1227   0.02534   0.01752  -0.1136   0.5675   0.0112
  -6.000  -0.0985   0.02365   0.01547  -0.1133   0.5581   0.0110
  -5.750  -0.0737   0.02221   0.01373  -0.1130   0.5494   0.0108
  -5.500  -0.0483   0.02100   0.01230  -0.1126   0.5420   0.0107
  -5.250  -0.0229   0.01999   0.01109  -0.1122   0.5340   0.0106
  -5.000   0.0029   0.01909   0.01008  -0.1120   0.5254   0.0106
  -4.750   0.0290   0.01831   0.00919  -0.1118   0.5151   0.0106
  -4.250   0.0821   0.01705   0.00765  -0.1119   0.4850   0.0108
  -4.000   0.1097   0.01655   0.00699  -0.1122   0.4714   0.0110
  -3.750   0.1384   0.01609   0.00640  -0.1126   0.4602   0.0113
  -3.500   0.1675   0.01570   0.00587  -0.1131   0.4427   0.0117
  -3.250   0.1955   0.01547   0.00541  -0.1133   0.4204   0.0122
  -3.000   0.2237   0.01530   0.00502  -0.1135   0.4055   0.0129
  -2.750   0.2530   0.01507   0.00466  -0.1139   0.3931   0.0143
  -2.250   0.3096   0.01487   0.00416  -0.1144   0.3449   0.0436
  -2.000   0.3391   0.01466   0.00397  -0.1150   0.3354   0.0976
  -1.750   0.3671   0.01466   0.00388  -0.1153   0.2961   0.1168
  -1.500   0.3959   0.01458   0.00380  -0.1158   0.2884   0.1645
  -1.250   0.4259   0.01434   0.00373  -0.1167   0.2823   0.2615
  -1.000   0.4561   0.01411   0.00371  -0.1176   0.2776   0.3307
  -0.500   0.5155   0.01383   0.00391  -0.1188   0.2523   0.5010
  -0.250   0.5419   0.01410   0.00407  -0.1186   0.2375   0.5137
   0.000   0.5690   0.01430   0.00421  -0.1185   0.2320   0.5282
   0.250   0.5963   0.01447   0.00432  -0.1184   0.2276   0.5448
   0.500   0.6240   0.01461   0.00443  -0.1184   0.2229   0.5581
   0.750   0.6514   0.01477   0.00454  -0.1183   0.2155   0.5685
   1.000   0.6792   0.01487   0.00465  -0.1183   0.1952   0.5774
   1.250   0.7041   0.01528   0.00491  -0.1179   0.1827   0.5852
   1.500   0.7301   0.01555   0.00512  -0.1177   0.1764   0.5929
   1.750   0.7569   0.01575   0.00530  -0.1175   0.1723   0.6017
   2.000   0.7835   0.01597   0.00550  -0.1174   0.1688   0.6148
   2.250   0.8098   0.01618   0.00574  -0.1172   0.1664   0.6285
   2.500   0.8362   0.01636   0.00595  -0.1169   0.1652   0.6398
   2.750   0.8631   0.01652   0.00613  -0.1168   0.1642   0.6487
   3.000   0.8896   0.01667   0.00633  -0.1166   0.1631   0.6544
   3.250   0.9161   0.01682   0.00655  -0.1164   0.1616   0.6614
   3.500   0.9428   0.01698   0.00675  -0.1163   0.1595   0.6684
   3.750   0.9698   0.01707   0.00693  -0.1162   0.1478   0.6757
   4.000   0.9942   0.01744   0.00726  -0.1158   0.1414   0.6840
   4.250   1.0173   0.01784   0.00767  -0.1151   0.1378   0.6913
   4.500   1.0412   0.01822   0.00802  -0.1146   0.1338   0.6999
   4.750   1.0649   0.01852   0.00838  -0.1140   0.1319   0.7075
   5.250   1.1126   0.01910   0.00911  -0.1129   0.1300   0.7275
   5.500   1.1362   0.01941   0.00949  -0.1123   0.1293   0.7387
   5.750   1.1595   0.01973   0.00990  -0.1117   0.1286   0.7509
   6.000   1.1817   0.02004   0.01032  -0.1109   0.1280   0.7622
   6.250   1.2036   0.02038   0.01076  -0.1100   0.1273   0.7739
   6.500   1.2251   0.02073   0.01121  -0.1092   0.1268   0.7864
   6.750   1.2457   0.02111   0.01170  -0.1081   0.1262   0.7995
   7.000   1.2652   0.02149   0.01219  -0.1069   0.1256   0.8128
   7.250   1.2835   0.02188   0.01270  -0.1055   0.1251   0.8284
   7.500   1.3002   0.02229   0.01323  -0.1038   0.1246   0.8483
   7.750   1.3136   0.02262   0.01372  -0.1014   0.1235   0.8762
   8.000   1.3224   0.02273   0.01401  -0.0980   0.1205   1.0000
   8.250   1.3423   0.02321   0.01457  -0.0972   0.1139   1.0000
   8.500   1.3636   0.02358   0.01505  -0.0965   0.1038   1.0000
   8.750   1.3748   0.02451   0.01595  -0.0946   0.0995   1.0000
   9.000   1.3826   0.02565   0.01700  -0.0925   0.0955   1.0000
   9.250   1.3885   0.02693   0.01826  -0.0903   0.0926   1.0000
   9.500   1.3964   0.02814   0.01952  -0.0885   0.0910   1.0000
   9.750   1.4052   0.02937   0.02082  -0.0870   0.0896   1.0000
  10.000   1.4127   0.03076   0.02233  -0.0855   0.0874   1.0000
  10.250   1.4148   0.03267   0.02434  -0.0840   0.0846   1.0000
  10.500   1.4111   0.03525   0.02699  -0.0827   0.0823   1.0000
  10.750   1.4404   0.03505   0.02700  -0.0828   0.0739   1.0000
  11.000   1.4463   0.03693   0.02893  -0.0820   0.0591   1.0000
  11.250   1.4431   0.03981   0.03173  -0.0813   0.0546   1.0000
  11.500   1.4438   0.04247   0.03448  -0.0809   0.0507   1.0000
  11.750   1.4422   0.04547   0.03758  -0.0806   0.0475   1.0000
  12.000   1.4448   0.04810   0.04033  -0.0805   0.0454   1.0000
  12.250   1.4524   0.05022   0.04259  -0.0805   0.0430   1.0000
  12.500   1.4577   0.05263   0.04512  -0.0806   0.0342   1.0000
  12.750   1.4506   0.05656   0.04904  -0.0808   0.0262   1.0000
  13.000   1.4478   0.06007   0.05259  -0.0811   0.0220   1.0000
  13.250   1.4471   0.06340   0.05599  -0.0815   0.0195   1.0000
  13.500   1.4471   0.06674   0.05942  -0.0820   0.0173   1.0000
  13.750   1.4464   0.07025   0.06303  -0.0826   0.0154   1.0000
  14.000   1.4456   0.07388   0.06676  -0.0833   0.0138   1.0000
  14.250   1.4454   0.07750   0.07051  -0.0842   0.0120   1.0000
  14.750   1.4365   0.08632   0.07949  -0.0866   0.0051   1.0000
  15.000   1.4297   0.09125   0.08451  -0.0881   0.0041   1.0000
  15.250   1.4253   0.09593   0.08931  -0.0897   0.0039   1.0000
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