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Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf)
Reynolds number: 100,000
Max Cl/Cd: 34.99 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0015-jf-100000.txt
Download as CSV file: xf-joukowsk0015-jf-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=15%                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9696   0.08180   0.07582  -0.0151   1.0000   0.1128
 -13.500  -1.0359   0.06960   0.06337  -0.0226   1.0000   0.1117
 -13.250  -1.0840   0.06183   0.05530  -0.0262   1.0000   0.1113
 -13.000  -1.1207   0.05649   0.04966  -0.0272   1.0000   0.1116
 -12.750  -1.1505   0.05261   0.04548  -0.0260   1.0000   0.1122
 -12.500  -1.1756   0.04951   0.04200  -0.0235   1.0000   0.1131
 -12.250  -1.1440   0.04814   0.04088  -0.0238   1.0000   0.1170
 -12.000  -1.1381   0.04625   0.03889  -0.0227   1.0000   0.1202
 -11.750  -1.1419   0.04375   0.03605  -0.0211   1.0000   0.1231
 -11.500  -1.1383   0.04129   0.03332  -0.0197   1.0000   0.1263
 -11.250  -1.1154   0.04018   0.03234  -0.0194   1.0000   0.1307
 -11.000  -1.1056   0.03843   0.03036  -0.0182   1.0000   0.1353
 -10.750  -1.0921   0.03652   0.02829  -0.0173   1.0000   0.1399
 -10.500  -1.0708   0.03549   0.02734  -0.0168   1.0000   0.1454
 -10.250  -1.0598   0.03390   0.02536  -0.0155   1.0000   0.1512
 -10.000  -1.0345   0.03274   0.02444  -0.0153   1.0000   0.1573
  -9.750  -1.0186   0.03149   0.02294  -0.0143   1.0000   0.1645
  -9.500  -0.9951   0.03036   0.02197  -0.0139   1.0000   0.1714
  -9.250  -0.9773   0.02928   0.02064  -0.0130   1.0000   0.1798
  -9.000  -0.9530   0.02831   0.01987  -0.0127   1.0000   0.1877
  -8.750  -0.9336   0.02725   0.01861  -0.0119   1.0000   0.1973
  -8.500  -0.9095   0.02649   0.01802  -0.0114   1.0000   0.2066
  -8.250  -0.8873   0.02558   0.01710  -0.0108   1.0000   0.2168
  -8.000  -0.8662   0.02483   0.01618  -0.0101   1.0000   0.2284
  -7.750  -0.8414   0.02414   0.01572  -0.0097   1.0000   0.2392
  -7.500  -0.8183   0.02342   0.01502  -0.0091   1.0000   0.2510
  -7.250  -0.7957   0.02274   0.01430  -0.0085   1.0000   0.2641
  -7.000  -0.7721   0.02221   0.01382  -0.0079   1.0000   0.2772
  -6.750  -0.7483   0.02168   0.01342  -0.0073   1.0000   0.2899
  -6.500  -0.7255   0.02114   0.01295  -0.0066   1.0000   0.3033
  -6.250  -0.7039   0.02065   0.01245  -0.0058   1.0000   0.3175
  -6.000  -0.6841   0.02025   0.01208  -0.0047   1.0000   0.3316
  -5.750  -0.6663   0.01990   0.01192  -0.0031   1.0000   0.3438
  -5.500  -0.6524   0.01956   0.01163  -0.0012   1.0000   0.3563
  -5.250  -0.6408   0.01929   0.01131   0.0009   1.0000   0.3697
  -5.000  -0.6278   0.01912   0.01128   0.0028   1.0000   0.3814
  -4.750  -0.6085   0.01896   0.01118   0.0035   0.9978   0.3951
  -4.500  -0.5566   0.01887   0.01116  -0.0014   0.9839   0.4157
  -4.250  -0.5048   0.01877   0.01113  -0.0061   0.9707   0.4361
  -4.000  -0.4532   0.01866   0.01108  -0.0105   0.9579   0.4564
  -3.750  -0.4052   0.01855   0.01104  -0.0140   0.9441   0.4755
  -3.500  -0.3622   0.01847   0.01101  -0.0164   0.9289   0.4933
  -3.250  -0.3245   0.01841   0.01101  -0.0177   0.9125   0.5100
  -3.000  -0.2926   0.01836   0.01099  -0.0177   0.8951   0.5258
  -2.750  -0.2651   0.01832   0.01094  -0.0170   0.8774   0.5415
  -2.500  -0.2401   0.01830   0.01088  -0.0157   0.8598   0.5575
  -2.250  -0.2157   0.01833   0.01100  -0.0140   0.8429   0.5705
  -2.000  -0.1921   0.01831   0.01100  -0.0123   0.8266   0.5845
  -1.750  -0.1688   0.01827   0.01092  -0.0106   0.8112   0.5997
  -1.500  -0.1452   0.01825   0.01087  -0.0091   0.7946   0.6154
  -1.250  -0.1212   0.01828   0.01097  -0.0074   0.7781   0.6282
  -1.000  -0.0971   0.01827   0.01098  -0.0059   0.7622   0.6426
  -0.750  -0.0730   0.01825   0.01093  -0.0045   0.7471   0.6581
  -0.500  -0.0489   0.01823   0.01086  -0.0029   0.7334   0.6735
  -0.250  -0.0246   0.01824   0.01093  -0.0013   0.7174   0.6868
   0.000   0.0000   0.01825   0.01096   0.0000   0.7017   0.7017
   0.250   0.0246   0.01824   0.01093   0.0013   0.6868   0.7174
   0.500   0.0489   0.01823   0.01086   0.0029   0.6735   0.7334
   0.750   0.0730   0.01825   0.01093   0.0045   0.6581   0.7470
   1.000   0.0971   0.01827   0.01098   0.0059   0.6426   0.7622
   1.250   0.1212   0.01828   0.01097   0.0074   0.6282   0.7781
   1.500   0.1452   0.01825   0.01087   0.0091   0.6154   0.7946
   1.750   0.1688   0.01827   0.01092   0.0106   0.5997   0.8112
   2.000   0.1921   0.01831   0.01100   0.0123   0.5845   0.8266
   2.250   0.2157   0.01833   0.01100   0.0140   0.5705   0.8429
   2.500   0.2401   0.01830   0.01088   0.0157   0.5575   0.8598
   2.750   0.2651   0.01832   0.01094   0.0170   0.5415   0.8774
   3.000   0.2926   0.01836   0.01098   0.0177   0.5258   0.8951
   3.250   0.3245   0.01840   0.01101   0.0177   0.5099   0.9125
   3.500   0.3622   0.01847   0.01102   0.0164   0.4934   0.9289
   3.750   0.4052   0.01855   0.01104   0.0140   0.4755   0.9441
   4.000   0.4533   0.01866   0.01108   0.0105   0.4564   0.9579
   4.250   0.5048   0.01877   0.01113   0.0060   0.4361   0.9707
   4.500   0.5566   0.01887   0.01116   0.0014   0.4156   0.9839
   4.750   0.6085   0.01896   0.01119  -0.0035   0.3951   0.9978
   5.000   0.6278   0.01912   0.01128  -0.0028   0.3814   1.0000
   5.250   0.6408   0.01929   0.01130  -0.0009   0.3697   1.0000
   5.500   0.6524   0.01956   0.01163   0.0012   0.3562   1.0000
   5.750   0.6664   0.01990   0.01192   0.0031   0.3438   1.0000
   6.000   0.6842   0.02025   0.01208   0.0047   0.3316   1.0000
   6.250   0.7039   0.02065   0.01245   0.0058   0.3175   1.0000
   6.500   0.7255   0.02114   0.01295   0.0066   0.3033   1.0000
   6.750   0.7483   0.02167   0.01342   0.0073   0.2899   1.0000
   7.000   0.7721   0.02221   0.01382   0.0079   0.2772   1.0000
   7.250   0.7957   0.02274   0.01429   0.0085   0.2641   1.0000
   7.500   0.8182   0.02341   0.01502   0.0091   0.2510   1.0000
   7.750   0.8414   0.02414   0.01571   0.0097   0.2392   1.0000
   8.000   0.8662   0.02483   0.01618   0.0101   0.2284   1.0000
   8.250   0.8873   0.02558   0.01709   0.0108   0.2167   1.0000
   8.500   0.9095   0.02649   0.01802   0.0114   0.2066   1.0000
   8.750   0.9337   0.02725   0.01860   0.0119   0.1973   1.0000
   9.000   0.9530   0.02831   0.01987   0.0127   0.1877   1.0000
   9.250   0.9774   0.02928   0.02064   0.0130   0.1798   1.0000
   9.500   0.9951   0.03035   0.02196   0.0139   0.1714   1.0000
   9.750   1.0186   0.03149   0.02294   0.0143   0.1645   1.0000
  10.000   1.0345   0.03273   0.02444   0.0153   0.1573   1.0000
  10.250   1.0598   0.03390   0.02536   0.0155   0.1512   1.0000
  10.500   1.0708   0.03548   0.02733   0.0168   0.1454   1.0000
  10.750   1.0923   0.03652   0.02829   0.0173   0.1399   1.0000
  11.000   1.1058   0.03844   0.03037   0.0182   0.1353   1.0000
  11.250   1.1156   0.04017   0.03234   0.0194   0.1307   1.0000
  11.500   1.1388   0.04129   0.03331   0.0197   0.1263   1.0000
  11.750   1.1421   0.04376   0.03607   0.0210   0.1231   1.0000
  12.000   1.1384   0.04626   0.03889   0.0227   0.1202   1.0000
  12.250   1.1445   0.04812   0.04086   0.0238   0.1170   1.0000
  12.500   1.1758   0.04952   0.04200   0.0234   0.1131   1.0000
  12.750   1.1508   0.05261   0.04548   0.0260   0.1122   1.0000
  13.000   1.1205   0.05654   0.04971   0.0271   0.1115   1.0000
  13.250   1.0843   0.06187   0.05535   0.0261   0.1113   1.0000
  13.500   1.0357   0.06971   0.06348   0.0224   0.1117   1.0000
  13.750   0.9679   0.08218   0.07620   0.0147   0.1128   1.0000
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