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NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)
Reynolds number: 50,000
Max Cl/Cd: 7.25 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls421mod-il-50000.txt
Download as CSV file: xf-ls421mod-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0421MOD AIRFOIL              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2531   0.13330   0.12560  -0.0269   1.0000   0.3345
 -11.750  -0.6557   0.07524   0.06728  -0.0631   1.0000   0.1597
 -11.500  -0.6924   0.07214   0.06420  -0.0594   1.0000   0.1590
 -11.250  -0.7318   0.07004   0.06211  -0.0542   1.0000   0.1583
 -11.000  -0.7690   0.06775   0.05977  -0.0493   1.0000   0.1578
 -10.750  -0.8021   0.06534   0.05724  -0.0447   1.0000   0.1575
 -10.500  -0.8299   0.06275   0.05445  -0.0407   1.0000   0.1578
 -10.250  -0.8520   0.06003   0.05146  -0.0372   1.0000   0.1585
 -10.000  -0.8687   0.05723   0.04826  -0.0343   1.0000   0.1596
  -9.750  -0.8585   0.05536   0.04654  -0.0326   1.0000   0.1630
  -9.500  -0.8532   0.05355   0.04467  -0.0308   1.0000   0.1664
  -9.250  -0.8510   0.05135   0.04223  -0.0291   1.0000   0.1701
  -9.000  -0.8493   0.04895   0.03931  -0.0278   1.0000   0.1745
  -8.750  -0.8341   0.04757   0.03817  -0.0265   1.0000   0.1805
  -8.500  -0.8226   0.04593   0.03633  -0.0255   1.0000   0.1875
  -8.250  -0.8087   0.04442   0.03482  -0.0244   1.0000   0.1952
  -8.000  -0.7947   0.04309   0.03333  -0.0236   1.0000   0.2054
  -7.750  -0.7791   0.04200   0.03244  -0.0224   1.0000   0.2163
  -7.500  -0.7636   0.04086   0.03133  -0.0214   1.0000   0.2301
  -7.250  -0.7478   0.03984   0.03038  -0.0205   1.0000   0.2468
  -7.000  -0.7321   0.03895   0.02968  -0.0193   1.0000   0.2668
  -6.750  -0.7165   0.03816   0.02915  -0.0182   1.0000   0.2911
  -6.500  -0.7002   0.03727   0.02847  -0.0174   1.0000   0.3231
  -6.250  -0.6845   0.03652   0.02812  -0.0163   1.0000   0.3633
  -6.000  -0.6537   0.03651   0.02887  -0.0165   0.9936   0.4273
  -5.750  -0.6248   0.03853   0.03150  -0.0138   0.9845   0.4905
  -5.500  -0.5923   0.04242   0.03558  -0.0100   0.9750   0.5363
  -5.250  -0.5624   0.04612   0.03924  -0.0061   0.9648   0.5691
  -5.000  -0.5297   0.05009   0.04312  -0.0021   0.9547   0.5946
  -4.750  -0.4929   0.05315   0.04603  -0.0005   0.9450   0.6260
  -4.500  -0.4644   0.05591   0.04869   0.0030   0.9351   0.6476
  -4.250  -0.4016   0.05936   0.05194   0.0023   0.9251   0.6729
  -4.000  -0.3776   0.06064   0.05312   0.0045   0.9152   0.6953
  -3.750  -0.3132   0.06230   0.05457   0.0008   0.9055   0.7249
  -3.500  -0.2894   0.06285   0.05503   0.0019   0.8954   0.7473
  -3.250  -0.2577   0.06314   0.05518   0.0008   0.8864   0.7734
  -3.000  -0.1550   0.06381   0.05564  -0.0099   0.8752   0.8009
  -2.750  -0.0975   0.06376   0.05545  -0.0151   0.8655   0.8298
  -2.500  -0.0190   0.06332   0.05485  -0.0240   0.8556   0.8578
  -2.250   0.0154   0.06296   0.05441  -0.0266   0.8454   0.8790
  -2.000   0.1121   0.06166   0.05293  -0.0391   0.8371   0.9079
  -1.750   0.1083   0.06196   0.05323  -0.0363   0.8256   0.9194
  -1.500   0.2076   0.06030   0.05143  -0.0497   0.8171   0.9434
  -1.250   0.1874   0.06128   0.05241  -0.0446   0.8056   0.9491
  -1.000   0.2555   0.06034   0.05139  -0.0532   0.7964   0.9640
  -0.750   0.2655   0.06091   0.05194  -0.0530   0.7855   0.9709
  -0.500   0.3102   0.06060   0.05159  -0.0579   0.7752   0.9803
  -0.250   0.3443   0.06085   0.05180  -0.0614   0.7650   0.9881
   0.000   0.3706   0.06121   0.05215  -0.0637   0.7538   0.9945
   0.250   0.4185   0.06108   0.05198  -0.0687   0.7443   1.0000
   0.500   0.3902   0.06290   0.05383  -0.0626   0.7334   1.0000
   0.750   0.4484   0.06185   0.05270  -0.0674   0.7258   1.0000
   1.000   0.3839   0.06501   0.05592  -0.0570   0.7148   1.0000
   1.250   0.4097   0.06506   0.05594  -0.0576   0.7061   1.0000
   1.500   0.3890   0.06679   0.05768  -0.0528   0.6969   1.0000
   1.750   0.3810   0.06801   0.05890  -0.0496   0.6880   1.0000
   2.000   0.4168   0.06792   0.05876  -0.0510   0.6794   1.0000
   2.250   0.3703   0.07039   0.06128  -0.0438   0.6704   1.0000
   2.500   0.4002   0.07043   0.06128  -0.0444   0.6613   1.0000
   2.750   0.3734   0.07237   0.06324  -0.0395   0.6529   1.0000
   3.000   0.3673   0.07351   0.06439  -0.0367   0.6439   1.0000
   3.250   0.3885   0.07395   0.06480  -0.0361   0.6345   1.0000
   3.500   0.3549   0.07599   0.06686  -0.0310   0.6266   1.0000
   3.750   0.4101   0.07522   0.06605  -0.0331   0.6152   1.0000
   4.000   0.3536   0.07805   0.06892  -0.0264   0.6085   1.0000
   4.250   0.3661   0.07851   0.06937  -0.0249   0.5980   1.0000
   4.500   0.3553   0.07988   0.07074  -0.0218   0.5890   1.0000
   4.750   0.3428   0.08116   0.07203  -0.0187   0.5804   1.0000
   5.000   0.2169   0.09076   0.08188  -0.0146   0.6783   1.0000
   5.250   0.2379   0.09187   0.08296  -0.0141   0.6578   1.0000
   5.500   0.2198   0.09283   0.08394  -0.0112   0.6564   1.0000
   5.750   0.2458   0.09436   0.08544  -0.0114   0.6364   1.0000
   6.000   0.2251   0.09527   0.08638  -0.0089   0.6335   1.0000
   6.250   0.3335   0.08798   0.07886  -0.0065   0.5215   1.0000
   6.500   0.3688   0.08841   0.07929  -0.0070   0.5073   1.0000
   6.750   0.3545   0.09153   0.08246  -0.0069   0.4987   1.0000
   7.000   0.3819   0.09277   0.08370  -0.0078   0.4849   1.0000
   7.250   0.3883   0.09540   0.08637  -0.0088   0.4748   1.0000
   7.500   0.4020   0.09771   0.08872  -0.0099   0.4628   1.0000
   7.750   0.4554   0.09753   0.08853  -0.0110   0.4480   1.0000
   8.000   0.4259   0.10318   0.09426  -0.0127   0.4426   1.0000
   8.250   0.4753   0.10331   0.09439  -0.0137   0.4277   1.0000
   8.500   0.4534   0.10903   0.10019  -0.0159   0.4245   1.0000
   8.750   0.4478   0.11368   0.10491  -0.0181   0.4226   1.0000
   9.000   0.4524   0.11849   0.10979  -0.0208   0.4249   1.0000
   9.250   0.4728   0.12343   0.11479  -0.0240   0.4279   1.0000
   9.500   0.5022   0.12477   0.11613  -0.0249   0.4086   1.0000
   9.750   0.4604   0.13746   0.12903  -0.0325   0.4696   1.0000
  10.000   0.4419   0.13893   0.13053  -0.0335   0.4648   1.0000
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