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FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 50,000
Max Cl/Cd: 27.69 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l100-il-50000.txt
Download as CSV file: xf-fx79l100-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-100                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7349   0.07979   0.07296  -0.0126   1.0000   0.1651
  -8.750  -0.7558   0.07204   0.06509  -0.0158   1.0000   0.1515
  -8.500  -0.7632   0.06627   0.05913  -0.0168   1.0000   0.1450
  -8.250  -0.7940   0.05954   0.05164  -0.0175   1.0000   0.1352
  -8.000  -0.7848   0.05483   0.04667  -0.0169   1.0000   0.1335
  -7.750  -0.7762   0.05039   0.04189  -0.0161   1.0000   0.1321
  -7.500  -0.7670   0.04638   0.03739  -0.0149   1.0000   0.1322
  -7.250  -0.7574   0.04311   0.03337  -0.0132   1.0000   0.1349
  -7.000  -0.7365   0.03980   0.03012  -0.0126   1.0000   0.1402
  -6.750  -0.7173   0.03679   0.02669  -0.0114   1.0000   0.1440
  -6.500  -0.6977   0.03418   0.02362  -0.0101   1.0000   0.1512
  -6.250  -0.6745   0.03193   0.02122  -0.0091   1.0000   0.1613
  -6.000  -0.6493   0.02959   0.01880  -0.0083   1.0000   0.1722
  -5.750  -0.6252   0.02768   0.01679  -0.0073   1.0000   0.1904
  -5.500  -0.5996   0.02568   0.01494  -0.0064   1.0000   0.2123
  -5.250  -0.5774   0.02384   0.01337  -0.0050   1.0000   0.2478
  -5.000  -0.5599   0.02169   0.01186  -0.0030   1.0000   0.3134
  -4.750  -0.5565   0.02009   0.01191   0.0030   1.0000   0.4946
  -4.500  -0.5497   0.02100   0.01315   0.0109   1.0000   0.6159
  -4.250  -0.5350   0.02185   0.01397   0.0172   1.0000   0.6764
  -4.000  -0.5168   0.02252   0.01458   0.0227   1.0000   0.7225
  -3.750  -0.4976   0.02296   0.01491   0.0277   1.0000   0.7640
  -3.500  -0.4616   0.02380   0.01554   0.0310   1.0000   0.8057
  -3.250  -0.4017   0.02455   0.01595   0.0295   1.0000   0.8467
  -3.000  -0.3278   0.02473   0.01569   0.0231   1.0000   0.8798
  -2.750  -0.2666   0.02429   0.01496   0.0171   1.0000   0.9043
  -2.500  -0.2099   0.02363   0.01406   0.0111   1.0000   0.9246
  -2.250  -0.1623   0.02290   0.01318   0.0063   1.0000   0.9430
  -2.000  -0.1153   0.02214   0.01230   0.0014   1.0000   0.9601
  -1.750  -0.0618   0.02125   0.01132  -0.0050   1.0000   0.9755
  -1.500  -0.0110   0.02039   0.01040  -0.0112   1.0000   0.9907
  -1.250   0.0279   0.01966   0.00967  -0.0154   1.0000   1.0000
  -1.000   0.0398   0.01926   0.00934  -0.0145   1.0000   1.0000
  -0.750   0.0486   0.01893   0.00911  -0.0133   1.0000   1.0000
  -0.500   0.0501   0.01873   0.00903  -0.0111   1.0000   1.0000
  -0.250   0.0351   0.01877   0.00916  -0.0068   1.0000   1.0000
   0.000   0.0000   0.01887   0.00929   0.0000   1.0000   1.0000
   0.250  -0.0351   0.01876   0.00916   0.0068   1.0000   1.0000
   0.500  -0.0502   0.01873   0.00903   0.0111   1.0000   1.0000
   0.750  -0.0487   0.01893   0.00911   0.0132   1.0000   1.0000
   1.000  -0.0399   0.01925   0.00933   0.0145   1.0000   1.0000
   1.250  -0.0280   0.01966   0.00967   0.0153   1.0000   1.0000
   1.500   0.0107   0.02039   0.01040   0.0112   0.9907   1.0000
   1.750   0.0616   0.02124   0.01131   0.0050   0.9755   1.0000
   2.000   0.1143   0.02213   0.01229  -0.0012   0.9603   1.0000
   2.250   0.1620   0.02290   0.01318  -0.0063   0.9433   1.0000
   2.500   0.2097   0.02363   0.01405  -0.0111   0.9247   1.0000
   2.750   0.2660   0.02429   0.01496  -0.0170   0.9044   1.0000
   3.000   0.3267   0.02474   0.01570  -0.0230   0.8805   1.0000
   3.250   0.4002   0.02459   0.01597  -0.0293   0.8474   1.0000
   3.500   0.4615   0.02378   0.01555  -0.0310   0.8056   1.0000
   3.750   0.4978   0.02295   0.01490  -0.0277   0.7643   1.0000
   4.000   0.5167   0.02250   0.01456  -0.0227   0.7225   1.0000
   4.250   0.5349   0.02186   0.01399  -0.0173   0.6768   1.0000
   4.500   0.5496   0.02098   0.01310  -0.0109   0.6157   1.0000
   4.750   0.5566   0.02010   0.01193  -0.0032   0.4963   1.0000
   5.000   0.5600   0.02168   0.01187   0.0029   0.3140   1.0000
   5.250   0.5774   0.02384   0.01337   0.0050   0.2481   1.0000
   5.500   0.5994   0.02567   0.01492   0.0064   0.2122   1.0000
   5.750   0.6253   0.02767   0.01678   0.0073   0.1909   1.0000
   6.000   0.6494   0.02958   0.01879   0.0083   0.1728   1.0000
   6.250   0.6746   0.03191   0.02118   0.0091   0.1617   1.0000
   6.500   0.6976   0.03414   0.02358   0.0101   0.1512   1.0000
   6.750   0.7173   0.03678   0.02668   0.0113   0.1440   1.0000
   7.000   0.7365   0.03981   0.03013   0.0126   0.1400   1.0000
   7.250   0.7571   0.04313   0.03341   0.0132   0.1348   1.0000
   7.500   0.7670   0.04640   0.03740   0.0149   0.1322   1.0000
   7.750   0.7758   0.05044   0.04195   0.0161   0.1320   1.0000
   8.000   0.7840   0.05491   0.04677   0.0170   0.1333   1.0000
   8.250   0.7857   0.05962   0.05194   0.0176   0.1365   1.0000
   8.500   0.7623   0.06634   0.05921   0.0167   0.1448   1.0000
   8.750   0.7502   0.07238   0.06545   0.0154   0.1521   1.0000
   9.000   0.7308   0.07987   0.07302   0.0125   0.1628   1.0000
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