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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 500,000
Max Cl/Cd: 70.97 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63143-il-500000.txt
Download as CSV file: xf-fx63143-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3811   0.08955   0.08745  -0.0414   1.0000   0.0179
  -9.750  -0.3879   0.08382   0.08176  -0.0445   1.0000   0.0181
  -9.500  -0.3998   0.07641   0.07439  -0.0495   1.0000   0.0182
  -9.250  -0.4167   0.06885   0.06683  -0.0560   1.0000   0.0181
  -9.000  -0.4328   0.06218   0.06007  -0.0614   0.9955   0.0181
  -8.750  -0.4557   0.05194   0.04929  -0.0680   0.9366   0.0184
  -8.500  -0.4169   0.04276   0.03944  -0.0811   0.8957   0.0186
  -8.250  -0.3950   0.03972   0.03604  -0.0833   0.8364   0.0187
  -8.000  -0.3900   0.03760   0.03363  -0.0810   0.8007   0.0188
  -7.750  -0.3835   0.03568   0.03144  -0.0787   0.7735   0.0189
  -7.500  -0.3759   0.03354   0.02902  -0.0763   0.7519   0.0191
  -7.250  -0.3666   0.03133   0.02651  -0.0740   0.7343   0.0193
  -7.000  -0.3550   0.02909   0.02396  -0.0718   0.7202   0.0196
  -6.750  -0.3411   0.02702   0.02156  -0.0697   0.7068   0.0199
  -6.500  -0.3257   0.02494   0.01909  -0.0676   0.6924   0.0202
  -6.250  -0.3065   0.02026   0.01364  -0.0645   0.6829   0.0132
  -6.000  -0.2840   0.01845   0.01158  -0.0634   0.6720   0.0123
  -5.750  -0.2607   0.01673   0.00948  -0.0621   0.6604   0.0114
  -5.500  -0.2372   0.01574   0.00842  -0.0614   0.6501   0.0112
  -5.250  -0.2144   0.01498   0.00757  -0.0604   0.6404   0.0110
  -5.000  -0.1919   0.01424   0.00677  -0.0595   0.6313   0.0109
  -4.750  -0.1696   0.01365   0.00611  -0.0585   0.6232   0.0108
  -4.500  -0.1465   0.01314   0.00554  -0.0577   0.6156   0.0109
  -4.250  -0.1233   0.01275   0.00506  -0.0568   0.6076   0.0111
  -3.750  -0.0741   0.01215   0.00433  -0.0557   0.5916   0.0124
  -3.500  -0.0479   0.01194   0.00406  -0.0554   0.5846   0.0134
  -3.250  -0.0220   0.01180   0.00384  -0.0550   0.5763   0.0139
  -3.000   0.0040   0.01165   0.00364  -0.0547   0.5668   0.0145
  -2.750   0.0299   0.01158   0.00348  -0.0544   0.5575   0.0152
  -2.500   0.0566   0.01156   0.00340  -0.0542   0.5480   0.0159
  -2.250   0.0819   0.01139   0.00316  -0.0538   0.5404   0.0173
  -2.000   0.1087   0.01130   0.00304  -0.0537   0.5339   0.0181
  -1.750   0.1350   0.01121   0.00290  -0.0535   0.5272   0.0187
  -1.500   0.1613   0.01103   0.00267  -0.0533   0.5208   0.0209
  -1.250   0.1881   0.01092   0.00254  -0.0532   0.5142   0.0217
  -0.750   0.2422   0.01081   0.00237  -0.0531   0.5019   0.0223
  -0.500   0.2691   0.01076   0.00228  -0.0530   0.4946   0.0234
  -0.250   0.2960   0.01074   0.00223  -0.0530   0.4864   0.0238
   0.000   0.3229   0.01073   0.00220  -0.0529   0.4780   0.0247
   0.250   0.3498   0.01071   0.00218  -0.0528   0.4705   0.0313
   0.500   0.3770   0.01072   0.00218  -0.0528   0.4617   0.0342
   0.750   0.4039   0.01072   0.00216  -0.0528   0.4540   0.0398
   1.000   0.4310   0.01068   0.00214  -0.0528   0.4441   0.0640
   1.250   0.4579   0.01071   0.00215  -0.0527   0.4345   0.0678
   1.500   0.4846   0.01076   0.00216  -0.0527   0.4250   0.0696
   1.750   0.5113   0.01081   0.00219  -0.0526   0.4151   0.0720
   2.000   0.5377   0.01087   0.00222  -0.0525   0.4062   0.0790
   2.250   0.5647   0.01091   0.00228  -0.0525   0.3960   0.0996
   2.500   0.5914   0.01098   0.00234  -0.0525   0.3845   0.1072
   2.750   0.6173   0.01099   0.00241  -0.0524   0.3669   0.1611
   3.000   0.6432   0.01062   0.00249  -0.0527   0.3531   0.3686
   3.250   0.6675   0.00951   0.00279  -0.0529   0.3427   0.8029
   3.500   0.6866   0.00969   0.00309  -0.0509   0.3333   0.8466
   3.750   0.7067   0.00999   0.00338  -0.0492   0.3164   0.8717
   4.000   0.7275   0.01043   0.00374  -0.0477   0.2956   0.8931
   4.250   0.7425   0.01072   0.00403  -0.0448   0.2873   0.9035
   4.500   0.7644   0.01097   0.00426  -0.0436   0.2805   0.9117
   4.750   0.7790   0.01116   0.00448  -0.0406   0.2756   0.9192
   5.000   0.8026   0.01136   0.00469  -0.0399   0.2661   0.9265
   5.250   0.8153   0.01154   0.00486  -0.0366   0.2489   0.9319
   5.500   0.8316   0.01180   0.00508  -0.0344   0.2390   0.9388
   5.750   0.8401   0.01191   0.00519  -0.0302   0.2334   0.9482
   6.000   0.8531   0.01211   0.00538  -0.0272   0.2235   0.9571
   6.250   0.8651   0.01219   0.00547  -0.0240   0.2148   0.9636
   6.500   0.8768   0.01262   0.00577  -0.0213   0.1831   0.9698
   6.750   0.8956   0.01285   0.00598  -0.0199   0.1736   0.9739
   7.000   0.9168   0.01309   0.00623  -0.0190   0.1654   0.9783
   7.250   0.9341   0.01349   0.00657  -0.0176   0.1386   0.9827
   7.500   0.9672   0.01405   0.00707  -0.0195   0.1291   0.9887
   7.750   1.0105   0.01446   0.00752  -0.0233   0.1231   0.9935
   8.250   1.0721   0.01569   0.00867  -0.0267   0.0923   1.0000
   8.500   1.0640   0.01590   0.00890  -0.0203   0.0903   1.0000
   8.750   1.0691   0.01622   0.00927  -0.0167   0.0881   1.0000
   9.000   1.0847   0.01659   0.00971  -0.0152   0.0864   1.0000
   9.250   1.1031   0.01699   0.01019  -0.0143   0.0841   1.0000
   9.500   1.1196   0.01757   0.01083  -0.0134   0.0797   1.0000
   9.750   1.1389   0.01805   0.01139  -0.0129   0.0744   1.0000
  10.000   1.1531   0.01886   0.01218  -0.0120   0.0643   1.0000
  10.250   1.1632   0.01998   0.01329  -0.0109   0.0597   1.0000
  10.500   1.1709   0.02137   0.01472  -0.0099   0.0567   1.0000
  10.750   1.1807   0.02271   0.01615  -0.0093   0.0532   1.0000
  11.000   1.1897   0.02422   0.01778  -0.0089   0.0493   1.0000
  11.250   1.2073   0.02511   0.01874  -0.0090   0.0367   1.0000
  11.500   1.2142   0.02692   0.02046  -0.0087   0.0295   1.0000
  11.750   1.2198   0.02892   0.02251  -0.0085   0.0271   1.0000
  12.000   1.2240   0.03110   0.02475  -0.0084   0.0253   1.0000
  12.250   1.2267   0.03349   0.02724  -0.0083   0.0238   1.0000
  12.500   1.2267   0.03618   0.03004  -0.0082   0.0228   1.0000
  12.750   1.2327   0.03833   0.03227  -0.0084   0.0223   1.0000
  13.000   1.2381   0.04054   0.03458  -0.0086   0.0215   1.0000
  13.250   1.2412   0.04302   0.03716  -0.0088   0.0211   1.0000
  13.500   1.2442   0.04554   0.03977  -0.0091   0.0203   1.0000
  13.750   1.2462   0.04823   0.04255  -0.0094   0.0198   1.0000
  14.000   1.2476   0.05104   0.04545  -0.0099   0.0192   1.0000
  14.250   1.2487   0.05397   0.04847  -0.0104   0.0186   1.0000
  14.500   1.2484   0.05713   0.05171  -0.0111   0.0182   1.0000
  14.750   1.2468   0.06051   0.05518  -0.0118   0.0176   1.0000
  15.000   1.2435   0.06422   0.05897  -0.0127   0.0171   1.0000
  15.250   1.2369   0.06836   0.06323  -0.0137   0.0165   1.0000
  15.500   1.2347   0.07203   0.06699  -0.0147   0.0162   1.0000
  15.750   1.2389   0.07500   0.07006  -0.0157   0.0159   1.0000
  16.000   1.2420   0.07813   0.07329  -0.0168   0.0154   1.0000
  16.250   1.2444   0.08142   0.07668  -0.0180   0.0148   1.0000
  16.500   1.2457   0.08490   0.08025  -0.0193   0.0141   1.0000
  16.750   1.2461   0.08858   0.08401  -0.0207   0.0133   1.0000
  17.000   1.2439   0.09268   0.08818  -0.0223   0.0127   1.0000
  17.250   1.2363   0.09749   0.09306  -0.0240   0.0118   1.0000
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