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FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-120 (fx79l120-il)
Reynolds number: 50,000
Max Cl/Cd: 27.94 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l120-il-50000.txt
Download as CSV file: xf-fx79l120-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6809   0.10034   0.09296  -0.0063   1.0000   0.1799
 -10.250  -0.6426   0.10024   0.09276  -0.0012   1.0000   0.1903
 -10.000  -0.7851   0.07613   0.06886  -0.0225   1.0000   0.1510
  -9.750  -0.8110   0.07079   0.06339  -0.0227   1.0000   0.1479
  -9.500  -0.8232   0.06573   0.05819  -0.0224   1.0000   0.1462
  -9.250  -0.8362   0.06088   0.05310  -0.0217   1.0000   0.1449
  -9.000  -0.8449   0.05643   0.04830  -0.0205   1.0000   0.1449
  -8.750  -0.8483   0.05241   0.04386  -0.0190   1.0000   0.1461
  -8.500  -0.8475   0.04871   0.03963  -0.0173   1.0000   0.1481
  -8.250  -0.8409   0.04522   0.03563  -0.0155   1.0000   0.1502
  -8.000  -0.8201   0.04220   0.03263  -0.0149   1.0000   0.1552
  -7.750  -0.8058   0.03964   0.02969  -0.0134   1.0000   0.1620
  -7.500  -0.7873   0.03692   0.02673  -0.0123   1.0000   0.1684
  -7.250  -0.7670   0.03475   0.02433  -0.0112   1.0000   0.1777
  -7.000  -0.7444   0.03261   0.02218  -0.0103   1.0000   0.1892
  -6.750  -0.7210   0.03059   0.02010  -0.0094   1.0000   0.2027
  -6.500  -0.6981   0.02879   0.01834  -0.0084   1.0000   0.2213
  -6.250  -0.6750   0.02698   0.01667  -0.0073   1.0000   0.2450
  -6.000  -0.6555   0.02527   0.01532  -0.0057   1.0000   0.2804
  -5.750  -0.6410   0.02355   0.01416  -0.0031   1.0000   0.3374
  -5.500  -0.6327   0.02264   0.01428   0.0016   1.0000   0.4381
  -5.250  -0.6213   0.02364   0.01573   0.0078   1.0000   0.5347
  -5.000  -0.6039   0.02498   0.01713   0.0132   1.0000   0.5921
  -4.750  -0.5834   0.02612   0.01823   0.0181   1.0000   0.6333
  -4.500  -0.5640   0.02692   0.01898   0.0227   1.0000   0.6684
  -4.250  -0.5405   0.02776   0.01976   0.0269   1.0000   0.7000
  -4.000  -0.5123   0.02854   0.02042   0.0305   1.0000   0.7299
  -3.750  -0.4807   0.02905   0.02081   0.0329   1.0000   0.7586
  -3.500  -0.4634   0.02886   0.02056   0.0358   1.0000   0.7846
  -3.250  -0.4055   0.02931   0.02075   0.0334   1.0000   0.8100
  -3.000  -0.3860   0.02886   0.02024   0.0346   1.0000   0.8313
  -2.750  -0.3475   0.02856   0.01981   0.0329   1.0000   0.8506
  -2.500  -0.2990   0.02819   0.01928   0.0289   1.0000   0.8682
  -2.250  -0.2672   0.02773   0.01875   0.0270   1.0000   0.8842
  -2.000  -0.2451   0.02731   0.01828   0.0263   1.0000   0.8994
  -1.750  -0.2208   0.02696   0.01787   0.0250   1.0000   0.9143
  -1.500  -0.1926   0.02666   0.01750   0.0227   1.0000   0.9291
  -1.250  -0.1563   0.02638   0.01717   0.0189   1.0000   0.9429
  -1.000  -0.1198   0.02614   0.01688   0.0148   1.0000   0.9572
  -0.750  -0.0816   0.02594   0.01666   0.0101   1.0000   0.9708
  -0.500  -0.0372   0.02576   0.01645   0.0041   1.0000   0.9846
  -0.250   0.0109   0.02563   0.01631  -0.0029   1.0000   0.9994
   0.000   0.0000   0.02569   0.01637   0.0000   1.0000   1.0000
   0.250  -0.0108   0.02563   0.01631   0.0029   0.9994   1.0000
   0.500   0.0373   0.02576   0.01645  -0.0040   0.9846   1.0000
   0.750   0.0818   0.02594   0.01665  -0.0101   0.9707   1.0000
   1.000   0.1202   0.02613   0.01688  -0.0148   0.9569   1.0000
   1.250   0.1563   0.02637   0.01716  -0.0189   0.9430   1.0000
   1.500   0.1932   0.02665   0.01750  -0.0228   0.9290   1.0000
   1.750   0.2199   0.02695   0.01786  -0.0248   0.9144   1.0000
   2.000   0.2445   0.02731   0.01828  -0.0262   0.8994   1.0000
   2.250   0.2700   0.02772   0.01875  -0.0274   0.8840   1.0000
   2.500   0.3014   0.02817   0.01928  -0.0292   0.8680   1.0000
   2.750   0.3485   0.02854   0.01980  -0.0330   0.8505   1.0000
   3.000   0.3858   0.02886   0.02024  -0.0346   0.8313   1.0000
   3.250   0.4055   0.02931   0.02075  -0.0334   0.8100   1.0000
   3.500   0.4636   0.02886   0.02056  -0.0358   0.7846   1.0000
   3.750   0.4815   0.02902   0.02079  -0.0329   0.7582   1.0000
   4.000   0.5122   0.02853   0.02042  -0.0304   0.7295   1.0000
   4.250   0.5404   0.02777   0.01977  -0.0269   0.6998   1.0000
   4.500   0.5640   0.02694   0.01900  -0.0226   0.6683   1.0000
   4.750   0.5834   0.02612   0.01823  -0.0180   0.6331   1.0000
   5.000   0.6041   0.02495   0.01709  -0.0132   0.5917   1.0000
   5.250   0.6213   0.02365   0.01573  -0.0078   0.5343   1.0000
   5.500   0.6328   0.02265   0.01428  -0.0016   0.4377   1.0000
   5.750   0.6411   0.02356   0.01417   0.0031   0.3374   1.0000
   6.000   0.6555   0.02527   0.01532   0.0057   0.2802   1.0000
   6.250   0.6752   0.02699   0.01668   0.0073   0.2450   1.0000
   6.500   0.6981   0.02879   0.01834   0.0084   0.2210   1.0000
   6.750   0.7209   0.03058   0.02009   0.0095   0.2023   1.0000
   7.000   0.7444   0.03262   0.02220   0.0104   0.1889   1.0000
   7.250   0.7668   0.03475   0.02434   0.0112   0.1774   1.0000
   7.500   0.7874   0.03694   0.02674   0.0123   0.1682   1.0000
   7.750   0.8055   0.03966   0.02972   0.0135   0.1617   1.0000
   8.000   0.8201   0.04222   0.03265   0.0149   0.1552   1.0000
   8.250   0.8409   0.04523   0.03565   0.0156   0.1502   1.0000
   8.500   0.8476   0.04874   0.03966   0.0173   0.1481   1.0000
   8.750   0.8484   0.05241   0.04386   0.0190   0.1460   1.0000
   9.000   0.8444   0.05646   0.04834   0.0206   0.1446   1.0000
   9.250   0.8361   0.06090   0.05311   0.0217   0.1448   1.0000
   9.500   0.8228   0.06580   0.05826   0.0224   0.1462   1.0000
   9.750   0.8102   0.07090   0.06350   0.0226   0.1479   1.0000
  10.000   0.7851   0.07623   0.06897   0.0224   0.1510   1.0000
  10.250   0.6436   0.10024   0.09276   0.0011   0.1904   1.0000
  10.500   0.6833   0.10023   0.09286   0.0064   0.1800   1.0000
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