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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.65 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63143-il-1000000-n5.txt
Download as CSV file: xf-fx63143-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4671   0.04178   0.03825  -0.0954   0.6364   0.0054
 -10.250  -0.4841   0.03866   0.03489  -0.0931   0.6230   0.0053
 -10.000  -0.4921   0.03659   0.03266  -0.0903   0.6197   0.0053
  -6.500  -0.3468   0.01600   0.00919  -0.0611   0.4881   0.0050
  -6.250  -0.3244   0.01516   0.00825  -0.0603   0.4830   0.0048
  -6.000  -0.3013   0.01454   0.00752  -0.0595   0.4769   0.0046
  -5.750  -0.2776   0.01406   0.00694  -0.0589   0.4692   0.0045
  -5.500  -0.2541   0.01363   0.00641  -0.0582   0.4574   0.0043
  -5.250  -0.2300   0.01328   0.00597  -0.0576   0.4429   0.0043
  -5.000  -0.2067   0.01304   0.00557  -0.0568   0.4172   0.0042
  -4.750  -0.1831   0.01282   0.00523  -0.0561   0.3934   0.0041
  -4.500  -0.1608   0.01276   0.00495  -0.0552   0.3453   0.0040
  -4.250  -0.1398   0.01283   0.00475  -0.0541   0.2772   0.0040
  -4.000  -0.1173   0.01282   0.00455  -0.0533   0.2224   0.0039
  -3.750  -0.0922   0.01260   0.00428  -0.0529   0.2130   0.0039
  -3.500  -0.0684   0.01252   0.00408  -0.0523   0.1724   0.0039
  -3.250  -0.0430   0.01232   0.00383  -0.0519   0.1657   0.0039
  -3.000  -0.0169   0.01215   0.00362  -0.0517   0.1615   0.0039
  -2.750   0.0087   0.01204   0.00344  -0.0514   0.1383   0.0040
  -2.500   0.0347   0.01194   0.00329  -0.0511   0.1296   0.0040
  -2.250   0.0613   0.01184   0.00315  -0.0510   0.1259   0.0041
  -2.000   0.0880   0.01176   0.00303  -0.0508   0.1219   0.0043
  -1.750   0.1147   0.01171   0.00295  -0.0507   0.1171   0.0045
  -1.500   0.1418   0.01166   0.00287  -0.0507   0.1146   0.0049
  -1.250   0.1687   0.01163   0.00282  -0.0506   0.1029   0.0052
  -1.000   0.1951   0.01165   0.00278  -0.0505   0.0931   0.0056
  -0.750   0.2220   0.01162   0.00271  -0.0504   0.0891   0.0066
  -0.500   0.2492   0.01164   0.00272  -0.0504   0.0871   0.0076
  -0.250   0.2764   0.01161   0.00270  -0.0504   0.0860   0.0107
   0.000   0.3035   0.01163   0.00270  -0.0504   0.0849   0.0114
   0.250   0.3306   0.01165   0.00271  -0.0504   0.0834   0.0118
   0.500   0.3577   0.01168   0.00273  -0.0504   0.0816   0.0122
   0.750   0.3847   0.01172   0.00276  -0.0504   0.0799   0.0130
   1.000   0.4117   0.01177   0.00281  -0.0504   0.0778   0.0137
   1.250   0.4389   0.01181   0.00284  -0.0504   0.0768   0.0153
   1.500   0.4661   0.01184   0.00286  -0.0505   0.0752   0.0176
   1.750   0.4928   0.01192   0.00291  -0.0504   0.0613   0.0182
   2.000   0.5194   0.01201   0.00297  -0.0504   0.0597   0.0191
   2.250   0.5462   0.01209   0.00302  -0.0504   0.0575   0.0200
   2.500   0.5731   0.01217   0.00310  -0.0504   0.0566   0.0203
   2.750   0.5999   0.01225   0.00318  -0.0503   0.0560   0.0208
   3.000   0.6266   0.01234   0.00329  -0.0503   0.0556   0.0222
   3.250   0.6533   0.01244   0.00340  -0.0503   0.0554   0.0326
   3.500   0.6798   0.01254   0.00352  -0.0503   0.0551   0.0351
   3.750   0.7063   0.01265   0.00364  -0.0503   0.0549   0.0374
   4.000   0.7327   0.01276   0.00377  -0.0502   0.0548   0.0415
   4.250   0.7591   0.01287   0.00392  -0.0502   0.0547   0.0598
   4.500   0.7853   0.01300   0.00407  -0.0501   0.0547   0.0659
   4.750   0.8113   0.01313   0.00423  -0.0500   0.0547   0.0720
   5.250   0.8627   0.01343   0.00462  -0.0498   0.0533   0.1010
   5.500   0.8880   0.01360   0.00484  -0.0496   0.0524   0.1098
   5.750   0.9135   0.01374   0.00507  -0.0494   0.0519   0.1497
   6.000   0.9389   0.01388   0.00530  -0.0493   0.0514   0.1906
   6.250   0.9654   0.01389   0.00559  -0.0497   0.0506   0.3206
   6.500   1.0053   0.01303   0.00612  -0.0536   0.0491   0.8287
   6.750   1.0268   0.01332   0.00651  -0.0526   0.0478   0.8587
   7.000   1.0483   0.01363   0.00688  -0.0517   0.0469   0.8711
   7.250   1.0717   0.01387   0.00715  -0.0511   0.0464   0.8798
   7.500   1.0953   0.01408   0.00739  -0.0506   0.0459   0.8873
   7.750   1.1204   0.01431   0.00763  -0.0504   0.0449   0.8928
   8.000   1.1420   0.01453   0.00790  -0.0495   0.0435   0.8969
   8.250   1.1625   0.01478   0.00820  -0.0484   0.0397   0.9032
   8.500   1.1780   0.01541   0.00870  -0.0466   0.0231   0.9087
   8.750   1.1927   0.01588   0.00918  -0.0446   0.0175   0.9126
   9.000   1.2054   0.01632   0.00965  -0.0423   0.0154   0.9148
   9.250   1.2187   0.01677   0.01013  -0.0401   0.0146   0.9173
   9.500   1.2306   0.01730   0.01068  -0.0378   0.0134   0.9204
   9.750   1.2429   0.01787   0.01128  -0.0357   0.0123   0.9238
  10.000   1.2556   0.01848   0.01194  -0.0338   0.0116   0.9264
  10.250   1.2624   0.01909   0.01262  -0.0309   0.0111   0.9307
  10.500   1.2715   0.01975   0.01334  -0.0286   0.0110   0.9341
  10.750   1.2809   0.02051   0.01417  -0.0266   0.0109   0.9373
  11.000   1.2904   0.02140   0.01511  -0.0250   0.0108   0.9401
  11.250   1.2997   0.02240   0.01617  -0.0235   0.0105   0.9423
  11.500   1.3071   0.02349   0.01734  -0.0220   0.0103   0.9445
  11.750   1.3142   0.02472   0.01864  -0.0207   0.0101   0.9462
  12.000   1.3214   0.02606   0.02005  -0.0196   0.0099   0.9479
  12.250   1.3283   0.02753   0.02159  -0.0187   0.0097   0.9496
  12.500   1.3346   0.02914   0.02328  -0.0179   0.0095   0.9512
  12.750   1.3409   0.03084   0.02504  -0.0173   0.0092   0.9527
  13.000   1.3465   0.03268   0.02695  -0.0168   0.0089   0.9542
  13.250   1.3521   0.03457   0.02890  -0.0165   0.0087   0.9555
  13.500   1.3560   0.03668   0.03107  -0.0162   0.0082   0.9566
  13.750   1.3577   0.03888   0.03334  -0.0157   0.0078   0.9587
  14.000   1.3587   0.04118   0.03572  -0.0153   0.0075   0.9606
  14.250   1.3591   0.04366   0.03828  -0.0150   0.0072   0.9622
  14.500   1.3627   0.04591   0.04061  -0.0150   0.0072   0.9638
  14.750   1.3681   0.04806   0.04282  -0.0151   0.0070   0.9652
  15.000   1.3727   0.05035   0.04518  -0.0153   0.0067   0.9667
  15.250   1.3767   0.05279   0.04769  -0.0156   0.0062   0.9682
  15.500   1.3792   0.05547   0.05045  -0.0160   0.0058   0.9696
  16.000   1.3813   0.06123   0.05629  -0.0170   0.0038   0.9734
  16.500   1.3774   0.06811   0.06326  -0.0186   0.0025   0.9779
  16.750   1.3780   0.07139   0.06663  -0.0196   0.0024   0.9800
  17.000   1.3781   0.07483   0.07015  -0.0208   0.0024   0.9818
  17.500   1.3744   0.08245   0.07794  -0.0235   0.0020   0.9923
  17.750   1.3697   0.08683   0.08240  -0.0252   0.0017   0.9998
  18.000   1.3670   0.09097   0.08662  -0.0268   0.0015   1.0000
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