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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 500,000
Max Cl/Cd: 64.21 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63143-il-500000-n5.txt
Download as CSV file: xf-fx63143-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2278   0.08199   0.07915  -0.0683   0.7922   0.0094
 -10.750  -0.2315   0.07750   0.07458  -0.0696   0.7693   0.0093
 -10.500  -0.3364   0.07905   0.07665  -0.0677   0.9023   0.0096
 -10.250  -0.3100   0.07026   0.06758  -0.0824   0.8465   0.0094
 -10.000  -0.3379   0.05844   0.05556  -0.0929   0.8189   0.0094
  -9.750  -0.3588   0.05382   0.05069  -0.0944   0.7867   0.0094
  -9.500  -0.3779   0.05041   0.04706  -0.0933   0.7612   0.0093
  -9.250  -0.4496   0.03984   0.03599  -0.0860   0.7542   0.0081
  -9.000  -0.4552   0.03755   0.03346  -0.0829   0.7370   0.0080
  -8.750  -0.4577   0.03513   0.03077  -0.0798   0.7206   0.0078
  -8.500  -0.4846   0.02668   0.02130  -0.0728   0.7099   0.0067
  -8.250  -0.4721   0.02513   0.01950  -0.0709   0.6946   0.0066
  -8.000  -0.4595   0.02324   0.01730  -0.0689   0.6814   0.0064
  -7.750  -0.4436   0.02166   0.01540  -0.0672   0.6677   0.0063
  -7.500  -0.4258   0.02025   0.01369  -0.0657   0.6536   0.0061
  -7.250  -0.4061   0.01911   0.01229  -0.0644   0.6397   0.0060
  -7.000  -0.3851   0.01820   0.01118  -0.0633   0.6279   0.0059
  -6.750  -0.3631   0.01750   0.01030  -0.0624   0.6176   0.0058
  -6.500  -0.3411   0.01688   0.00949  -0.0614   0.6061   0.0057
  -6.250  -0.3183   0.01632   0.00881  -0.0606   0.5963   0.0056
  -6.000  -0.2953   0.01581   0.00818  -0.0598   0.5869   0.0056
  -5.750  -0.2722   0.01539   0.00765  -0.0591   0.5729   0.0055
  -5.500  -0.2491   0.01495   0.00711  -0.0583   0.5613   0.0055
  -5.250  -0.2257   0.01458   0.00665  -0.0576   0.5513   0.0054
  -5.000  -0.2023   0.01421   0.00619  -0.0569   0.5435   0.0054
  -4.750  -0.1782   0.01386   0.00579  -0.0563   0.5368   0.0054
  -4.500  -0.1539   0.01351   0.00538  -0.0558   0.5311   0.0054
  -4.250  -0.1297   0.01321   0.00501  -0.0552   0.5238   0.0054
  -4.000  -0.1048   0.01291   0.00466  -0.0547   0.5144   0.0054
  -3.750  -0.0799   0.01267   0.00436  -0.0543   0.5067   0.0055
  -3.500  -0.0544   0.01242   0.00406  -0.0539   0.4996   0.0055
  -3.250  -0.0292   0.01223   0.00378  -0.0535   0.4904   0.0056
  -3.000  -0.0037   0.01208   0.00356  -0.0532   0.4778   0.0057
  -2.750   0.0219   0.01195   0.00335  -0.0528   0.4653   0.0058
  -2.500   0.0474   0.01186   0.00316  -0.0525   0.4471   0.0060
  -2.250   0.0727   0.01183   0.00301  -0.0521   0.4254   0.0063
  -2.000   0.0984   0.01179   0.00287  -0.0518   0.4105   0.0066
  -1.750   0.1244   0.01176   0.00278  -0.0516   0.3967   0.0071
  -1.500   0.1500   0.01182   0.00275  -0.0513   0.3710   0.0126
  -1.250   0.1752   0.01195   0.00276  -0.0509   0.3480   0.0136
  -1.000   0.2010   0.01198   0.00271  -0.0507   0.3321   0.0138
  -0.750   0.2244   0.01223   0.00275  -0.0501   0.2866   0.0141
  -0.500   0.2502   0.01229   0.00275  -0.0499   0.2723   0.0149
  -0.250   0.2729   0.01262   0.00287  -0.0492   0.2213   0.0153
   0.000   0.2985   0.01272   0.00289  -0.0489   0.1944   0.0155
   0.250   0.3233   0.01289   0.00296  -0.0486   0.1770   0.0159
   0.500   0.3496   0.01292   0.00295  -0.0484   0.1695   0.0164
   0.750   0.3758   0.01297   0.00297  -0.0483   0.1631   0.0183
   1.000   0.4018   0.01301   0.00296  -0.0481   0.1407   0.0211
   1.500   0.4536   0.01321   0.00309  -0.0478   0.1299   0.0328
   1.750   0.4801   0.01329   0.00316  -0.0477   0.1262   0.0336
   2.000   0.5066   0.01337   0.00325  -0.0476   0.1226   0.0346
   2.250   0.5327   0.01348   0.00335  -0.0475   0.1177   0.0358
   2.500   0.5591   0.01357   0.00344  -0.0474   0.1143   0.0370
   2.750   0.5846   0.01372   0.00357  -0.0472   0.0964   0.0386
   3.000   0.6105   0.01384   0.00369  -0.0471   0.0949   0.0416
   3.250   0.6363   0.01396   0.00383  -0.0469   0.0933   0.0619
   3.500   0.6620   0.01409   0.00396  -0.0467   0.0914   0.0686
   3.750   0.6878   0.01419   0.00411  -0.0466   0.0898   0.0987
   4.000   0.7138   0.01425   0.00427  -0.0466   0.0886   0.1506
   4.250   0.7433   0.01355   0.00444  -0.0481   0.0877   0.4923
   4.500   0.7708   0.01286   0.00480  -0.0486   0.0871   0.8038
   4.750   0.7887   0.01303   0.00513  -0.0465   0.0868   0.8469
   5.000   0.8113   0.01324   0.00539  -0.0455   0.0864   0.8631
   5.250   0.8346   0.01345   0.00564  -0.0448   0.0860   0.8745
   5.500   0.8568   0.01368   0.00591  -0.0438   0.0857   0.8861
   5.750   0.8778   0.01394   0.00621  -0.0425   0.0849   0.8981
   6.000   0.8984   0.01421   0.00652  -0.0412   0.0816   0.9051
   6.250   0.9222   0.01452   0.00684  -0.0409   0.0779   0.9088
   6.500   0.9452   0.01472   0.00708  -0.0402   0.0756   0.9116
   6.750   0.9633   0.01509   0.00744  -0.0387   0.0616   0.9142
   7.000   0.9807   0.01545   0.00779  -0.0370   0.0600   0.9182
   7.250   0.9987   0.01584   0.00819  -0.0355   0.0582   0.9239
   7.500   1.0128   0.01614   0.00854  -0.0331   0.0572   0.9298
   7.750   1.0236   0.01642   0.00886  -0.0300   0.0562   0.9357
   8.000   1.0390   0.01677   0.00926  -0.0281   0.0549   0.9404
   8.250   1.0527   0.01710   0.00965  -0.0259   0.0540   0.9440
   8.500   1.0620   0.01741   0.01004  -0.0228   0.0531   0.9492
   8.750   1.0736   0.01779   0.01049  -0.0203   0.0524   0.9555
   9.000   1.0846   0.01819   0.01097  -0.0178   0.0515   0.9595
   9.250   1.0934   0.01864   0.01149  -0.0151   0.0508   0.9649
   9.500   1.1048   0.01925   0.01218  -0.0132   0.0495   0.9688
   9.750   1.1125   0.02005   0.01306  -0.0111   0.0477   0.9732
  10.000   1.1221   0.02083   0.01391  -0.0093   0.0463   0.9789
  10.250   1.1429   0.02124   0.01441  -0.0092   0.0439   0.9822
  10.500   1.1611   0.02201   0.01521  -0.0092   0.0325   0.9870
  11.000   1.1814   0.02483   0.01804  -0.0087   0.0225   1.0000
  11.250   1.1911   0.02639   0.01966  -0.0085   0.0198   1.0000
  11.500   1.1983   0.02823   0.02154  -0.0083   0.0174   1.0000
  11.750   1.2063   0.03005   0.02343  -0.0083   0.0163   1.0000
  12.000   1.2149   0.03186   0.02531  -0.0084   0.0158   1.0000
  12.250   1.2226   0.03377   0.02731  -0.0085   0.0152   1.0000
  12.500   1.2292   0.03582   0.02945  -0.0086   0.0149   1.0000
  12.750   1.2346   0.03800   0.03171  -0.0087   0.0143   1.0000
  13.000   1.2389   0.04032   0.03410  -0.0089   0.0138   1.0000
  13.250   1.2436   0.04262   0.03649  -0.0091   0.0136   1.0000
  13.500   1.2458   0.04522   0.03915  -0.0094   0.0129   1.0000
  13.750   1.2477   0.04790   0.04192  -0.0098   0.0124   1.0000
  14.000   1.2485   0.05078   0.04487  -0.0102   0.0120   1.0000
  14.250   1.2487   0.05381   0.04800  -0.0108   0.0115   1.0000
  14.500   1.2486   0.05696   0.05125  -0.0114   0.0112   1.0000
  14.750   1.2525   0.05968   0.05406  -0.0121   0.0110   1.0000
  15.000   1.2568   0.06242   0.05689  -0.0129   0.0108   1.0000
  15.250   1.2602   0.06532   0.05989  -0.0138   0.0105   1.0000
  15.500   1.2619   0.06849   0.06315  -0.0147   0.0104   1.0000
  15.750   1.2647   0.07154   0.06631  -0.0157   0.0101   1.0000
  16.000   1.2661   0.07488   0.06974  -0.0168   0.0098   1.0000
  16.250   1.2680   0.07817   0.07313  -0.0179   0.0094   1.0000
  16.500   1.2695   0.08156   0.07661  -0.0192   0.0090   1.0000
  16.750   1.2706   0.08508   0.08022  -0.0205   0.0086   1.0000
  17.000   1.2710   0.08873   0.08396  -0.0219   0.0083   1.0000
  17.250   1.2702   0.09264   0.08795  -0.0235   0.0079   1.0000
  17.500   1.2684   0.09674   0.09214  -0.0252   0.0076   1.0000
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