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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 50,000
Max Cl/Cd: 42.55 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63110-il-50000-n5.txt
Download as CSV file: xf-fx63110-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-110 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3202   0.11530   0.10801  -0.0384   1.0000   0.1174
  -9.500  -0.3287   0.10896   0.10169  -0.0421   1.0000   0.0777
  -9.000  -0.3493   0.10063   0.09359  -0.0458   1.0000   0.0672
  -8.750  -0.3464   0.09774   0.09077  -0.0447   1.0000   0.0665
  -8.500  -0.3527   0.09483   0.08798  -0.0444   1.0000   0.0665
  -8.250  -0.3605   0.09220   0.08546  -0.0435   1.0000   0.0663
  -8.000  -0.3724   0.08980   0.08318  -0.0421   1.0000   0.0662
  -7.750  -0.3877   0.08748   0.08100  -0.0406   1.0000   0.0662
  -7.500  -0.3990   0.08480   0.07845  -0.0399   1.0000   0.0660
  -7.250  -0.4108   0.08154   0.07528  -0.0404   1.0000   0.0659
  -7.000  -0.4201   0.07766   0.07148  -0.0422   1.0000   0.0657
  -6.750  -0.4262   0.07267   0.06651  -0.0461   1.0000   0.0655
  -6.500  -0.4227   0.06662   0.06036  -0.0526   0.9982   0.0653
  -6.250  -0.3934   0.05796   0.05127  -0.0660   0.9907   0.0652
  -6.000  -0.3509   0.04886   0.04113  -0.0812   0.9847   0.0673
  -5.750  -0.3206   0.04603   0.03826  -0.0845   0.9790   0.0703
  -5.500  -0.2811   0.04204   0.03375  -0.0906   0.9742   0.0723
  -5.250  -0.2412   0.03881   0.02993  -0.0957   0.9689   0.0764
  -5.000  -0.1956   0.03582   0.02606  -0.1012   0.9650   0.0806
  -4.750  -0.1630   0.03378   0.02386  -0.1032   0.9589   0.0831
  -4.500  -0.1252   0.03231   0.02216  -0.1060   0.9540   0.0884
  -4.250  -0.0904   0.03103   0.02043  -0.1078   0.9477   0.0943
  -4.000  -0.0560   0.02974   0.01906  -0.1093   0.9423   0.0986
  -3.750  -0.0228   0.02880   0.01801  -0.1105   0.9364   0.1048
  -3.500   0.0094   0.02800   0.01711  -0.1116   0.9298   0.1145
  -3.250   0.0477   0.02716   0.01617  -0.1138   0.9251   0.1268
  -3.000   0.0790   0.02643   0.01546  -0.1151   0.9174   0.1424
  -2.750   0.1214   0.02544   0.01466  -0.1187   0.9124   0.1807
  -2.500   0.1652   0.02429   0.01444  -0.1230   0.9077   0.3451
  -2.250   0.1948   0.02422   0.01479  -0.1231   0.8995   0.4693
  -2.000   0.2306   0.02442   0.01503  -0.1237   0.8940   0.5443
  -1.750   0.2541   0.02474   0.01535  -0.1224   0.8840   0.5955
  -1.250   0.3078   0.02510   0.01569  -0.1202   0.8677   0.6804
  -1.000   0.3419   0.02498   0.01550  -0.1205   0.8620   0.7087
  -0.750   0.3662   0.02505   0.01548  -0.1198   0.8515   0.7293
  -0.500   0.4019   0.02484   0.01518  -0.1207   0.8457   0.7497
  -0.250   0.4243   0.02493   0.01522  -0.1197   0.8349   0.7699
   0.000   0.4595   0.02470   0.01492  -0.1204   0.8292   0.7921
   0.250   0.4788   0.02480   0.01502  -0.1188   0.8180   0.8134
   0.500   0.5064   0.02466   0.01487  -0.1183   0.8104   0.8379
   1.000   0.5509   0.02451   0.01477  -0.1157   0.7914   0.9008
   1.250   0.5866   0.02426   0.01452  -0.1169   0.7832   1.0000
   1.500   0.6204   0.02461   0.01479  -0.1188   0.7728   1.0000
   1.750   0.6632   0.02460   0.01469  -0.1215   0.7662   1.0000
   2.000   0.6930   0.02501   0.01507  -0.1224   0.7547   1.0000
   2.250   0.7278   0.02521   0.01523  -0.1238   0.7456   1.0000
   2.500   0.7625   0.02537   0.01535  -0.1250   0.7363   1.0000
   2.750   0.7913   0.02574   0.01574  -0.1254   0.7249   1.0000
   3.000   0.8263   0.02582   0.01581  -0.1264   0.7159   1.0000
   3.250   0.8567   0.02607   0.01609  -0.1267   0.7049   1.0000
   3.500   0.8841   0.02642   0.01649  -0.1267   0.6926   1.0000
   3.750   0.9144   0.02662   0.01671  -0.1269   0.6813   1.0000
   4.000   0.9498   0.02648   0.01662  -0.1274   0.6709   1.0000
   4.250   0.9770   0.02666   0.01685  -0.1270   0.6563   1.0000
   4.500   1.0044   0.02679   0.01704  -0.1265   0.6413   1.0000
   4.750   1.0315   0.02694   0.01727  -0.1259   0.6261   1.0000
   5.000   1.0582   0.02712   0.01753  -0.1253   0.6108   1.0000
   5.250   1.0845   0.02734   0.01782  -0.1247   0.5954   1.0000
   5.500   1.1105   0.02757   0.01816  -0.1240   0.5796   1.0000
   5.750   1.1362   0.02781   0.01849  -0.1232   0.5633   1.0000
   6.000   1.1618   0.02804   0.01881  -0.1224   0.5465   1.0000
   6.250   1.1855   0.02836   0.01925  -0.1214   0.5283   1.0000
   6.500   1.2060   0.02876   0.01975  -0.1199   0.5065   1.0000
   6.750   1.2281   0.02893   0.01989  -0.1183   0.4815   1.0000
   7.000   1.2467   0.02930   0.02023  -0.1164   0.4534   1.0000
   7.250   1.2628   0.02990   0.02084  -0.1143   0.4243   1.0000
   7.500   1.2783   0.03065   0.02160  -0.1123   0.3968   1.0000
   7.750   1.2923   0.03153   0.02246  -0.1102   0.3692   1.0000
   8.000   1.3035   0.03254   0.02346  -0.1079   0.3404   1.0000
   8.250   1.3118   0.03372   0.02458  -0.1053   0.3115   1.0000
   8.500   1.3162   0.03509   0.02585  -0.1024   0.2822   1.0000
   8.750   1.3190   0.03673   0.02740  -0.0997   0.2539   1.0000
   9.000   1.3212   0.03859   0.02916  -0.0971   0.2281   1.0000
   9.250   1.3222   0.04070   0.03111  -0.0948   0.2060   1.0000
   9.500   1.3248   0.04289   0.03329  -0.0929   0.1857   1.0000
   9.750   1.3275   0.04520   0.03558  -0.0912   0.1690   1.0000
  10.000   1.3309   0.04758   0.03795  -0.0897   0.1548   1.0000
  10.250   1.3350   0.05000   0.04038  -0.0883   0.1430   1.0000
  10.500   1.3396   0.05243   0.04282  -0.0871   0.1340   1.0000
  10.750   1.3480   0.05474   0.04527  -0.0860   0.1248   1.0000
  11.000   1.3556   0.05710   0.04767  -0.0849   0.1177   1.0000
  11.250   1.3635   0.05949   0.05018  -0.0840   0.1107   1.0000
  11.500   1.3729   0.06184   0.05260  -0.0831   0.1049   1.0000
  11.750   1.3844   0.06419   0.05516  -0.0822   0.0997   1.0000
  12.000   1.3986   0.06627   0.05724  -0.0813   0.0955   1.0000
  12.250   1.4088   0.06902   0.06029  -0.0805   0.0916   1.0000
  12.500   1.4134   0.07216   0.06372  -0.0800   0.0878   1.0000
  12.750   1.4200   0.07501   0.06669  -0.0795   0.0845   1.0000
  13.000   1.4348   0.07751   0.06920  -0.0788   0.0814   1.0000
  13.250   1.4278   0.08211   0.07423  -0.0788   0.0796   1.0000
  13.500   1.4176   0.08714   0.07964  -0.0793   0.0779   1.0000
  13.750   1.4055   0.09251   0.08533  -0.0804   0.0762   1.0000
  14.000   1.3923   0.09819   0.09129  -0.0819   0.0747   1.0000
  14.250   1.3784   0.10417   0.09750  -0.0840   0.0734   1.0000
  14.500   1.3639   0.11049   0.10404  -0.0866   0.0723   1.0000
  14.750   1.3483   0.11737   0.11112  -0.0899   0.0714   1.0000
  15.000   1.3501   0.12139   0.11515  -0.0910   0.0695   1.0000
  15.250   1.3208   0.13162   0.12563  -0.0974   0.0696   1.0000
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