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NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)A-015 (naca632a015-il)
Reynolds number: 50,000
Max Cl/Cd: 23.29 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca632a015-il-50000.txt
Download as CSV file: xf-naca632a015-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)A-015                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5020   0.07862   0.07218  -0.0332   1.0000   0.2383
  -8.500  -0.5658   0.07307   0.06680  -0.0334   1.0000   0.2330
  -8.250  -0.6215   0.06968   0.06346  -0.0297   1.0000   0.2310
  -8.000  -0.6425   0.06454   0.05817  -0.0281   1.0000   0.2071
  -7.750  -0.6885   0.06199   0.05530  -0.0224   1.0000   0.1996
  -7.500  -0.6935   0.05829   0.05129  -0.0193   1.0000   0.1788
  -7.000  -0.7178   0.05358   0.04558  -0.0097   1.0000   0.1524
  -6.750  -0.7085   0.05065   0.04252  -0.0072   1.0000   0.1450
  -6.500  -0.7105   0.04869   0.04001  -0.0029   1.0000   0.1373
  -6.250  -0.7060   0.04742   0.03825   0.0008   1.0000   0.1335
  -6.000  -0.6955   0.04489   0.03553   0.0031   1.0000   0.1317
  -5.750  -0.6837   0.04270   0.03310   0.0055   1.0000   0.1297
  -5.500  -0.6692   0.04072   0.03083   0.0077   1.0000   0.1270
  -5.250  -0.6531   0.03895   0.02873   0.0098   1.0000   0.1251
  -5.000  -0.6356   0.03739   0.02692   0.0115   1.0000   0.1261
  -4.750  -0.6170   0.03604   0.02535   0.0131   1.0000   0.1288
  -4.500  -0.5960   0.03482   0.02390   0.0145   1.0000   0.1314
  -4.250  -0.5746   0.03389   0.02272   0.0159   1.0000   0.1346
  -4.000  -0.5454   0.03219   0.02132   0.0160   1.0000   0.1428
  -3.750  -0.5246   0.03146   0.02050   0.0174   1.0000   0.1513
  -3.500  -0.5087   0.03037   0.01958   0.0193   1.0000   0.1615
  -3.250  -0.4975   0.02953   0.01876   0.0216   1.0000   0.1720
  -3.000  -0.4874   0.02868   0.01793   0.0240   1.0000   0.1854
  -2.750  -0.4770   0.02765   0.01709   0.0260   1.0000   0.2077
  -2.500  -0.4763   0.02540   0.01646   0.0292   1.0000   0.3925
  -2.250  -0.4780   0.02532   0.01755   0.0367   1.0000   0.6574
  -2.000  -0.1398   0.03821   0.02964   0.0083   1.0000   0.9613
  -1.750  -0.1160   0.03813   0.02942   0.0059   1.0000   0.9719
  -1.500  -0.0536   0.03799   0.02905  -0.0036   0.9906   0.9803
  -1.250   0.0128   0.03783   0.02868  -0.0138   0.9802   0.9892
  -1.000   0.0817   0.03766   0.02833  -0.0244   0.9706   0.9984
  -0.750   0.1190   0.03753   0.02812  -0.0291   0.9586   1.0000
  -0.500   0.1484   0.03751   0.02802  -0.0322   0.9461   1.0000
  -0.250   0.1760   0.03755   0.02800  -0.0349   0.9339   1.0000
   0.000   0.2084   0.03764   0.02802  -0.0381   0.9222   1.0000
   0.250   0.2417   0.03771   0.02804  -0.0413   0.9097   1.0000
   0.500   0.2589   0.03789   0.02820  -0.0416   0.8958   1.0000
   0.750   0.2787   0.03810   0.02838  -0.0422   0.8820   1.0000
   1.000   0.3029   0.03829   0.02855  -0.0433   0.8679   1.0000
   1.250   0.3326   0.03842   0.02867  -0.0450   0.8535   1.0000
   1.500   0.3685   0.03845   0.02868  -0.0473   0.8384   1.0000
   1.750   0.4114   0.03829   0.02853  -0.0504   0.8225   1.0000
   2.000   0.4626   0.03789   0.02816  -0.0543   0.8064   1.0000
   2.250   0.4939   0.03771   0.02801  -0.0549   0.7900   1.0000
   2.500   0.5106   0.03785   0.02816  -0.0533   0.7736   1.0000
   2.750   0.5293   0.03790   0.02825  -0.0518   0.7569   1.0000
   3.000   0.5474   0.03791   0.02828  -0.0501   0.7401   1.0000
   3.250   0.5642   0.03793   0.02832  -0.0480   0.7233   1.0000
   3.500   0.5826   0.03783   0.02825  -0.0459   0.7063   1.0000
   3.750   0.6048   0.03752   0.02799  -0.0440   0.6890   1.0000
   4.000   0.6287   0.03711   0.02760  -0.0421   0.6717   1.0000
   4.250   0.6473   0.03685   0.02736  -0.0396   0.6540   1.0000
   4.500   0.6461   0.03735   0.02787  -0.0349   0.6346   1.0000
   4.750   0.6562   0.03747   0.02802  -0.0314   0.6157   1.0000
   5.000   0.6720   0.03742   0.02798  -0.0285   0.5972   1.0000
   5.250   0.6936   0.03714   0.02771  -0.0262   0.5788   1.0000
   5.500   0.7178   0.03681   0.02738  -0.0242   0.5610   1.0000
   5.750   0.7418   0.03656   0.02715  -0.0223   0.5437   1.0000
   6.000   0.7656   0.03639   0.02697  -0.0205   0.5266   1.0000
   6.250   0.7844   0.03659   0.02717  -0.0183   0.5103   1.0000
   6.500   0.7992   0.03713   0.02774  -0.0159   0.4949   1.0000
   6.750   0.8126   0.03781   0.02844  -0.0134   0.4801   1.0000
   7.000   0.8274   0.03850   0.02914  -0.0112   0.4659   1.0000
   7.250   0.8480   0.03893   0.02959  -0.0095   0.4525   1.0000
   7.500   0.8751   0.03900   0.02966  -0.0084   0.4387   1.0000
   7.750   0.9062   0.03891   0.02954  -0.0078   0.4247   1.0000
   8.000   0.8972   0.04103   0.03180  -0.0036   0.4130   1.0000
   8.250   0.8963   0.04288   0.03374  -0.0004   0.4018   1.0000
   8.500   0.9209   0.04330   0.03418   0.0008   0.3893   1.0000
   8.750   0.9533   0.04336   0.03424   0.0012   0.3758   1.0000
   9.000   0.9128   0.04766   0.03872   0.0071   0.3689   1.0000
   9.250   0.9328   0.04841   0.03953   0.0086   0.3565   1.0000
   9.500   0.8910   0.05310   0.04428   0.0136   0.3508   1.0000
   9.750   0.8220   0.06102   0.05213   0.0173   0.3478   1.0000
  10.000   0.7181   0.07734   0.06822   0.0135   0.3459   1.0000
  10.250   0.6633   0.08797   0.07873   0.0102   0.3441   1.0000
  10.500   0.6319   0.09550   0.08619   0.0080   0.3425   1.0000
  10.750   0.6132   0.10153   0.09221   0.0062   0.3409   1.0000
  11.000   0.6020   0.10696   0.09766   0.0047   0.3407   1.0000
  11.250   0.5983   0.11217   0.10291   0.0031   0.3428   1.0000
  11.500   0.6009   0.11713   0.10793   0.0018   0.3445   1.0000
  11.750   0.6200   0.11928   0.11017   0.0026   0.3296   1.0000
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