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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.43 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63143-il-1000000.txt
Download as CSV file: xf-fx63143-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-143 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2678   0.08649   0.08427  -0.0757   0.8337   0.0125
 -10.500  -0.2703   0.08231   0.07971  -0.0777   0.7493   0.0127
 -10.250  -0.2753   0.07703   0.07437  -0.0806   0.7291   0.0130
 -10.000  -0.2823   0.07107   0.06841  -0.0845   0.7242   0.0129
  -9.250  -0.3572   0.03584   0.03270  -0.0894   0.6779   0.0135
  -9.000  -0.3777   0.03351   0.03023  -0.0854   0.6701   0.0135
  -8.750  -0.4011   0.03059   0.02705  -0.0807   0.6650   0.0136
  -8.500  -0.4138   0.02761   0.02377  -0.0768   0.6575   0.0136
  -8.250  -0.4247   0.02467   0.02045  -0.0726   0.6503   0.0136
  -7.500  -0.3978   0.02897   0.02429  -0.0721   0.6272   0.0139
  -7.250  -0.3812   0.02768   0.02292  -0.0711   0.6196   0.0141
  -7.000  -0.3652   0.02627   0.02136  -0.0697   0.6121   0.0145
  -6.750  -0.3490   0.02451   0.01937  -0.0680   0.6056   0.0148
  -6.500  -0.3348   0.02299   0.01724  -0.0650   0.5983   0.0158
  -6.250  -0.3190   0.02207   0.01583  -0.0629   0.5919   0.0159
  -6.000  -0.2942   0.01820   0.01181  -0.0622   0.5853   0.0139
  -5.750  -0.2690   0.01561   0.00895  -0.0612   0.5755   0.0114
  -5.500  -0.2444   0.01429   0.00762  -0.0607   0.5653   0.0110
  -5.250  -0.2287   0.01204   0.00526  -0.0584   0.5571   0.0097
  -5.000  -0.2076   0.01130   0.00442  -0.0572   0.5482   0.0093
  -4.750  -0.1840   0.01088   0.00388  -0.0564   0.5390   0.0089
  -4.500  -0.1585   0.01064   0.00354  -0.0560   0.5306   0.0086
  -4.250  -0.1326   0.01048   0.00329  -0.0556   0.5199   0.0084
  -4.000  -0.1065   0.01036   0.00310  -0.0553   0.5073   0.0082
  -3.750  -0.0798   0.01025   0.00294  -0.0551   0.4966   0.0080
  -3.500  -0.0530   0.01019   0.00284  -0.0550   0.4865   0.0079
  -3.250  -0.0264   0.01015   0.00273  -0.0548   0.4750   0.0078
  -3.000   0.0005   0.01009   0.00264  -0.0546   0.4628   0.0076
  -2.750   0.0273   0.01005   0.00256  -0.0545   0.4495   0.0075
  -2.500   0.0534   0.01007   0.00248  -0.0543   0.4274   0.0075
  -2.250   0.0799   0.01007   0.00241  -0.0541   0.4130   0.0075
  -2.000   0.1065   0.01006   0.00233  -0.0539   0.3987   0.0076
  -1.750   0.1318   0.01016   0.00232  -0.0536   0.3643   0.0081
  -1.500   0.1573   0.01029   0.00232  -0.0533   0.3399   0.0115
  -1.250   0.1813   0.01054   0.00237  -0.0527   0.2917   0.0128
  -1.000   0.2058   0.01078   0.00245  -0.0522   0.2474   0.0134
  -0.750   0.2306   0.01100   0.00254  -0.0519   0.2194   0.0144
  -0.500   0.2566   0.01108   0.00256  -0.0517   0.1915   0.0149
  -0.250   0.2822   0.01122   0.00260  -0.0514   0.1726   0.0153
   0.000   0.3089   0.01132   0.00267  -0.0513   0.1634   0.0159
   0.250   0.3349   0.01135   0.00263  -0.0512   0.1389   0.0164
   0.500   0.3612   0.01141   0.00263  -0.0510   0.1304   0.0168
   0.750   0.3882   0.01143   0.00264  -0.0510   0.1253   0.0177
   1.000   0.4149   0.01150   0.00268  -0.0510   0.1179   0.0186
   1.250   0.4420   0.01151   0.00265  -0.0510   0.1127   0.0208
   1.500   0.4681   0.01162   0.00271  -0.0508   0.0951   0.0308
   1.750   0.4947   0.01173   0.00279  -0.0508   0.0914   0.0333
   2.000   0.5217   0.01180   0.00286  -0.0508   0.0891   0.0357
   2.250   0.5488   0.01187   0.00294  -0.0508   0.0875   0.0371
   2.500   0.5758   0.01193   0.00301  -0.0508   0.0869   0.0377
   2.750   0.6029   0.01200   0.00308  -0.0509   0.0866   0.0389
   3.000   0.6299   0.01207   0.00317  -0.0509   0.0864   0.0404
   3.250   0.6569   0.01215   0.00326  -0.0509   0.0861   0.0432
   3.500   0.6838   0.01222   0.00337  -0.0510   0.0859   0.0604
   3.750   0.7106   0.01231   0.00348  -0.0510   0.0858   0.0670
   4.000   0.7375   0.01237   0.00361  -0.0510   0.0856   0.0971
   4.250   0.7642   0.01246   0.00374  -0.0510   0.0856   0.1098
   4.500   0.7918   0.01236   0.00389  -0.0514   0.0855   0.2376
   4.750   0.8232   0.01183   0.00406  -0.0531   0.0854   0.5138
   5.000   0.8590   0.01129   0.00432  -0.0557   0.0835   0.7762
   5.250   0.8818   0.01141   0.00468  -0.0548   0.0803   0.8505
   5.500   0.9047   0.01166   0.00498  -0.0539   0.0782   0.8725
   5.750   0.9288   0.01186   0.00522  -0.0533   0.0773   0.8835
   6.000   0.9546   0.01207   0.00544  -0.0531   0.0760   0.8918
   6.250   0.9770   0.01230   0.00569  -0.0522   0.0671   0.8975
   6.500   0.9953   0.01271   0.00606  -0.0504   0.0611   0.9058
   6.750   1.0173   0.01307   0.00641  -0.0496   0.0592   0.9110
   7.000   1.0358   0.01334   0.00671  -0.0479   0.0582   0.9148
   7.250   1.0544   0.01362   0.00703  -0.0462   0.0572   0.9193
   7.500   1.0748   0.01394   0.00736  -0.0450   0.0561   0.9239
   7.750   1.0957   0.01425   0.00770  -0.0440   0.0550   0.9275
   8.000   1.1116   0.01449   0.00800  -0.0419   0.0543   0.9308
   8.250   1.1261   0.01476   0.00833  -0.0395   0.0537   0.9356
   8.500   1.1424   0.01509   0.00871  -0.0376   0.0527   0.9407
   8.750   1.1493   0.01530   0.00899  -0.0337   0.0515   0.9463
   9.000   1.1583   0.01564   0.00940  -0.0305   0.0500   0.9509
   9.250   1.1699   0.01615   0.00996  -0.0280   0.0480   0.9545
   9.500   1.1913   0.01636   0.01020  -0.0274   0.0452   0.9565
   9.750   1.2010   0.01660   0.01035  -0.0245   0.0287   0.9609
  10.000   1.2060   0.01725   0.01099  -0.0212   0.0222   0.9650
  10.250   1.2112   0.01791   0.01169  -0.0181   0.0195   0.9704
  10.500   1.2152   0.01859   0.01242  -0.0150   0.0177   0.9758
  10.750   1.2203   0.01939   0.01327  -0.0124   0.0164   0.9821
  11.000   1.2333   0.02026   0.01421  -0.0116   0.0160   0.9908
  11.250   1.2473   0.02133   0.01535  -0.0114   0.0156   1.0000
  11.500   1.2605   0.02253   0.01662  -0.0112   0.0152   1.0000
  11.750   1.2725   0.02388   0.01804  -0.0111   0.0149   1.0000
  12.000   1.2836   0.02536   0.01959  -0.0110   0.0145   1.0000
  12.250   1.2933   0.02700   0.02129  -0.0110   0.0141   1.0000
  12.500   1.3017   0.02881   0.02317  -0.0110   0.0138   1.0000
  12.750   1.3089   0.03076   0.02519  -0.0111   0.0134   1.0000
  13.000   1.3147   0.03288   0.02738  -0.0112   0.0129   1.0000
  13.250   1.3201   0.03505   0.02962  -0.0113   0.0127   1.0000
  13.500   1.3226   0.03756   0.03221  -0.0114   0.0122   1.0000
  13.750   1.3237   0.04024   0.03498  -0.0116   0.0118   1.0000
  14.000   1.3229   0.04313   0.03798  -0.0118   0.0115   1.0000
  14.500   1.3262   0.04863   0.04366  -0.0127   0.0111   1.0000
  14.750   1.3355   0.05062   0.04569  -0.0132   0.0109   1.0000
  15.000   1.3431   0.05283   0.04796  -0.0138   0.0106   1.0000
  15.250   1.3492   0.05526   0.05046  -0.0145   0.0101   1.0000
  15.500   1.3526   0.05803   0.05330  -0.0152   0.0098   1.0000
  15.750   1.3577   0.06064   0.05596  -0.0159   0.0092   1.0000
  16.000   1.3612   0.06350   0.05888  -0.0168   0.0086   1.0000
  16.250   1.3609   0.06688   0.06230  -0.0178   0.0077   1.0000
  16.500   1.3633   0.06997   0.06545  -0.0188   0.0071   1.0000
  16.750   1.3733   0.07210   0.06764  -0.0197   0.0064   1.0000
  17.000   1.3761   0.07524   0.07084  -0.0208   0.0059   1.0000
  17.250   1.3815   0.07802   0.07363  -0.0219   0.0049   1.0000
  17.500   1.3807   0.08172   0.07737  -0.0232   0.0044   1.0000
  17.750   1.3795   0.08553   0.08123  -0.0247   0.0038   1.0000
  18.000   1.3788   0.08931   0.08505  -0.0262   0.0034   1.0000
  18.250   1.3756   0.09357   0.08938  -0.0279   0.0031   1.0000
  18.500   1.3719   0.09795   0.09385  -0.0297   0.0031   1.0000
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