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LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LDS-2 AIRFOIL (lds2-il)
Reynolds number: 50,000
Max Cl/Cd: 33.99 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lds2-il-50000.txt
Download as CSV file: xf-lds2-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LDS-2 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3788   0.11221   0.10490  -0.0185   1.0000   0.3004
  -9.500  -0.3817   0.10971   0.10248  -0.0185   1.0000   0.3119
  -9.250  -0.3993   0.10924   0.10212  -0.0184   1.0000   0.3248
  -9.000  -0.3803   0.10500   0.09789  -0.0174   1.0000   0.3397
  -8.750  -0.2916   0.09527   0.08883  -0.0208   1.0000   0.3567
  -8.500  -0.2661   0.09037   0.08391  -0.0204   1.0000   0.3652
  -8.250  -0.2724   0.08762   0.08126  -0.0194   1.0000   0.3752
  -8.000  -0.2884   0.08610   0.07987  -0.0177   1.0000   0.3881
  -7.750  -0.2721   0.08151   0.07529  -0.0173   1.0000   0.3918
  -7.500  -0.3452   0.08660   0.07985  -0.0123   1.0000   0.4109
  -6.750  -0.5582   0.06345   0.05700  -0.0316   1.0000   0.1800
  -6.500  -0.5694   0.05833   0.05160  -0.0308   1.0000   0.1620
  -6.250  -0.5773   0.05366   0.04642  -0.0295   1.0000   0.1484
  -6.000  -0.5757   0.04992   0.04234  -0.0277   1.0000   0.1423
  -5.750  -0.5725   0.04673   0.03835  -0.0257   1.0000   0.1357
  -5.500  -0.5618   0.04391   0.03526  -0.0240   1.0000   0.1346
  -5.250  -0.5492   0.04127   0.03229  -0.0224   1.0000   0.1333
  -5.000  -0.5342   0.03886   0.02952  -0.0208   1.0000   0.1316
  -4.750  -0.5171   0.03661   0.02688  -0.0193   1.0000   0.1307
  -4.500  -0.4986   0.03480   0.02466  -0.0179   1.0000   0.1323
  -4.250  -0.4792   0.03334   0.02276  -0.0165   1.0000   0.1355
  -4.000  -0.4586   0.03171   0.02094  -0.0153   1.0000   0.1389
  -3.750  -0.4373   0.03032   0.01949  -0.0142   1.0000   0.1433
  -3.500  -0.4162   0.02931   0.01828  -0.0129   1.0000   0.1512
  -3.250  -0.3956   0.02816   0.01724  -0.0117   1.0000   0.1613
  -3.000  -0.3746   0.02716   0.01628  -0.0104   1.0000   0.1755
  -2.750  -0.3531   0.02618   0.01537  -0.0094   1.0000   0.2000
  -2.500  -0.3336   0.02464   0.01445  -0.0084   1.0000   0.2628
  -2.250  -0.3374   0.02257   0.01498   0.0004   1.0000   0.6993
  -2.000  -0.1313   0.02606   0.01804  -0.0205   1.0000   1.0000
  -1.750  -0.1576   0.02504   0.01702  -0.0157   1.0000   1.0000
  -1.500  -0.1792   0.02409   0.01598  -0.0110   1.0000   1.0000
  -1.250  -0.1802   0.02377   0.01540  -0.0086   1.0000   1.0000
  -1.000  -0.1712   0.02382   0.01517  -0.0071   1.0000   1.0000
  -0.750  -0.1584   0.02403   0.01510  -0.0061   1.0000   1.0000
  -0.500  -0.1438   0.02434   0.01517  -0.0052   1.0000   1.0000
  -0.250  -0.1282   0.02471   0.01532  -0.0044   1.0000   1.0000
   0.000  -0.1120   0.02514   0.01555  -0.0038   1.0000   1.0000
   0.250  -0.0955   0.02561   0.01583  -0.0032   1.0000   1.0000
   0.500  -0.0787   0.02613   0.01619  -0.0026   1.0000   1.0000
   0.750  -0.0456   0.02717   0.01705  -0.0052   0.9941   1.0000
   1.000  -0.0077   0.02834   0.01806  -0.0087   0.9850   1.0000
   1.250   0.0255   0.02935   0.01896  -0.0113   0.9761   1.0000
   1.500   0.0576   0.03038   0.01989  -0.0137   0.9667   1.0000
   1.750   0.0910   0.03150   0.02092  -0.0162   0.9570   1.0000
   2.000   0.1297   0.03281   0.02215  -0.0196   0.9461   1.0000
   2.250   0.1613   0.03380   0.02311  -0.0217   0.9331   1.0000
   2.500   0.1966   0.03487   0.02416  -0.0242   0.9180   1.0000
   2.750   0.2313   0.03593   0.02521  -0.0265   0.9024   1.0000
   3.000   0.2641   0.03698   0.02626  -0.0284   0.8871   1.0000
   3.250   0.2975   0.03801   0.02732  -0.0303   0.8712   1.0000
   3.500   0.3323   0.03901   0.02837  -0.0322   0.8543   1.0000
   3.750   0.3729   0.03995   0.02938  -0.0347   0.8359   1.0000
   4.000   0.4087   0.04073   0.03023  -0.0362   0.8159   1.0000
   4.250   0.4382   0.04135   0.03095  -0.0365   0.7938   1.0000
   4.500   0.4929   0.04149   0.03124  -0.0395   0.7707   1.0000
   4.750   0.5216   0.04177   0.03164  -0.0390   0.7462   1.0000
   5.000   0.5868   0.04076   0.03089  -0.0418   0.7223   1.0000
   5.250   0.6202   0.04031   0.03060  -0.0409   0.6955   1.0000
   5.500   0.6915   0.03753   0.02815  -0.0423   0.6689   1.0000
   5.750   0.7733   0.03305   0.02401  -0.0432   0.6415   1.0000
   6.000   0.8111   0.03079   0.02191  -0.0404   0.6046   1.0000
   6.250   0.8544   0.02799   0.01918  -0.0377   0.5555   1.0000
   6.500   0.8819   0.02643   0.01735  -0.0337   0.4891   1.0000
   6.750   0.9000   0.02648   0.01679  -0.0299   0.4197   1.0000
   7.000   0.9155   0.02765   0.01742  -0.0271   0.3643   1.0000
   7.250   0.9345   0.02914   0.01854  -0.0253   0.3237   1.0000
   7.500   0.9574   0.03085   0.01999  -0.0243   0.2921   1.0000
   7.750   0.9848   0.03265   0.02151  -0.0240   0.2676   1.0000
   8.000   1.0066   0.03446   0.02337  -0.0231   0.2490   1.0000
   8.250   1.0305   0.03641   0.02533  -0.0225   0.2342   1.0000
   8.500   1.0544   0.03840   0.02726  -0.0220   0.2208   1.0000
   8.750   1.0677   0.04052   0.02979  -0.0200   0.2114   1.0000
   9.000   1.0875   0.04293   0.03232  -0.0191   0.2030   1.0000
   9.250   1.1000   0.04521   0.03489  -0.0173   0.1950   1.0000
   9.500   1.1170   0.04798   0.03777  -0.0163   0.1889   1.0000
   9.750   1.1165   0.05102   0.04131  -0.0133   0.1853   1.0000
  10.000   1.1189   0.05398   0.04460  -0.0109   0.1811   1.0000
  10.250   1.1407   0.05689   0.04742  -0.0106   0.1749   1.0000
  10.500   1.1273   0.06049   0.05149  -0.0072   0.1736   1.0000
  10.750   1.1108   0.06447   0.05584  -0.0040   0.1731   1.0000
  11.000   1.0877   0.06871   0.06036  -0.0008   0.1732   1.0000
  11.250   1.0601   0.07301   0.06482   0.0022   0.1738   1.0000
  11.500   1.0319   0.07801   0.06996   0.0039   0.1746   1.0000
  11.750   1.0068   0.08379   0.07583   0.0041   0.1754   1.0000
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