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LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LDS-2 AIRFOIL (lds2-il)
Reynolds number: 100,000
Max Cl/Cd: 50.34 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lds2-il-100000-n5.txt
Download as CSV file: xf-lds2-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4590   0.08934   0.08399  -0.0432   1.0000   0.0352
 -10.000  -0.5323   0.06867   0.06319  -0.0601   1.0000   0.0313
  -9.750  -0.5568   0.06428   0.05873  -0.0614   1.0000   0.0313
  -9.500  -0.5773   0.06137   0.05577  -0.0595   1.0000   0.0313
  -9.250  -0.5896   0.05867   0.05301  -0.0574   1.0000   0.0311
  -9.000  -0.6081   0.05548   0.04965  -0.0546   1.0000   0.0312
  -8.750  -0.6204   0.05266   0.04665  -0.0515   1.0000   0.0312
  -8.500  -0.6308   0.05004   0.04385  -0.0480   1.0000   0.0312
  -8.250  -0.6394   0.04762   0.04123  -0.0442   1.0000   0.0311
  -8.000  -0.6448   0.04518   0.03852  -0.0408   0.9996   0.0312
  -7.750  -0.6245   0.04114   0.03391  -0.0425   0.9913   0.0314
  -7.500  -0.5996   0.03803   0.03050  -0.0441   0.9845   0.0319
  -7.250  -0.5740   0.03585   0.02811  -0.0453   0.9771   0.0326
  -7.000  -0.5459   0.03405   0.02609  -0.0466   0.9704   0.0342
  -6.750  -0.5180   0.03191   0.02354  -0.0476   0.9636   0.0357
  -6.500  -0.4893   0.02980   0.02101  -0.0483   0.9572   0.0367
  -6.250  -0.4589   0.02792   0.01873  -0.0490   0.9509   0.0376
  -6.000  -0.4246   0.02618   0.01689  -0.0507   0.9469   0.0390
  -5.750  -0.3967   0.02515   0.01580  -0.0511   0.9392   0.0413
  -5.500  -0.3636   0.02401   0.01451  -0.0523   0.9339   0.0439
  -5.250  -0.3317   0.02290   0.01324  -0.0530   0.9282   0.0458
  -5.000  -0.3046   0.02180   0.01221  -0.0532   0.9208   0.0480
  -4.750  -0.2723   0.02097   0.01136  -0.0542   0.9157   0.0523
  -4.500  -0.2475   0.02025   0.01057  -0.0537   0.9072   0.0561
  -4.250  -0.2187   0.01948   0.00979  -0.0541   0.9011   0.0609
  -4.000  -0.1930   0.01889   0.00915  -0.0538   0.8934   0.0682
  -3.750  -0.1656   0.01830   0.00849  -0.0537   0.8864   0.0789
  -3.500  -0.1396   0.01758   0.00790  -0.0535   0.8797   0.1014
  -3.250  -0.1192   0.01642   0.00734  -0.0527   0.8715   0.2101
  -3.000  -0.0986   0.01532   0.00719  -0.0516   0.8653   0.4301
  -2.750  -0.0771   0.01509   0.00717  -0.0502   0.8569   0.5141
  -2.500  -0.0511   0.01484   0.00713  -0.0493   0.8515   0.5883
  -2.250  -0.0317   0.01470   0.00727  -0.0470   0.8433   0.6617
  -2.000  -0.0057   0.01456   0.00725  -0.0458   0.8372   0.7121
  -1.750   0.0234   0.01448   0.00713  -0.0457   0.8312   0.7354
  -1.500   0.0516   0.01443   0.00707  -0.0455   0.8242   0.7583
  -1.250   0.0840   0.01434   0.00694  -0.0459   0.8192   0.7833
  -1.000   0.1134   0.01435   0.00695  -0.0459   0.8121   0.8102
  -0.750   0.1476   0.01435   0.00693  -0.0468   0.8062   0.8381
  -0.500   0.1865   0.01432   0.00686  -0.0485   0.8018   0.8654
  -0.250   0.2235   0.01441   0.00693  -0.0502   0.7939   0.8911
   0.000   0.2641   0.01442   0.00687  -0.0525   0.7879   0.9140
   0.250   0.3052   0.01447   0.00687  -0.0550   0.7809   0.9339
   0.500   0.3467   0.01450   0.00685  -0.0577   0.7740   0.9516
   0.750   0.3893   0.01451   0.00679  -0.0607   0.7687   0.9672
   1.000   0.4297   0.01460   0.00687  -0.0635   0.7610   0.9832
   1.250   0.4738   0.01456   0.00680  -0.0669   0.7551   0.9961
   1.500   0.4998   0.01465   0.00687  -0.0669   0.7460   1.0000
   1.750   0.5226   0.01464   0.00679  -0.0657   0.7377   1.0000
   2.000   0.5413   0.01473   0.00687  -0.0640   0.7259   1.0000
   2.250   0.5619   0.01476   0.00687  -0.0624   0.7137   1.0000
   2.500   0.5833   0.01475   0.00682  -0.0609   0.7003   1.0000
   2.750   0.6049   0.01475   0.00677  -0.0594   0.6865   1.0000
   3.000   0.6271   0.01477   0.00675  -0.0579   0.6732   1.0000
   3.250   0.6480   0.01484   0.00683  -0.0564   0.6589   1.0000
   3.500   0.6691   0.01491   0.00689  -0.0549   0.6435   1.0000
   3.750   0.6904   0.01497   0.00693  -0.0533   0.6265   1.0000
   4.000   0.7107   0.01507   0.00702  -0.0516   0.6072   1.0000
   4.250   0.7308   0.01518   0.00714  -0.0499   0.5862   1.0000
   4.500   0.7512   0.01529   0.00720  -0.0482   0.5627   1.0000
   4.750   0.7702   0.01546   0.00734  -0.0463   0.5341   1.0000
   5.000   0.7887   0.01568   0.00747  -0.0443   0.4986   1.0000
   5.250   0.8055   0.01600   0.00762  -0.0420   0.4506   1.0000
   5.500   0.8198   0.01652   0.00783  -0.0394   0.3969   1.0000
   5.750   0.8318   0.01724   0.00822  -0.0367   0.3388   1.0000
   6.000   0.8431   0.01806   0.00874  -0.0340   0.2937   1.0000
   6.250   0.8561   0.01884   0.00933  -0.0316   0.2571   1.0000
   6.500   0.8695   0.01961   0.00994  -0.0294   0.2266   1.0000
   6.750   0.8832   0.02038   0.01056  -0.0273   0.2023   1.0000
   7.000   0.8975   0.02112   0.01121  -0.0253   0.1826   1.0000
   7.250   0.9116   0.02187   0.01190  -0.0232   0.1666   1.0000
   7.500   0.9257   0.02262   0.01261  -0.0212   0.1535   1.0000
   7.750   0.9393   0.02340   0.01334  -0.0192   0.1431   1.0000
   8.000   0.9530   0.02417   0.01409  -0.0172   0.1335   1.0000
   8.250   0.9664   0.02493   0.01488  -0.0152   0.1255   1.0000
   8.500   0.9782   0.02576   0.01569  -0.0130   0.1188   1.0000
   8.750   0.9919   0.02660   0.01656  -0.0111   0.1128   1.0000
   9.000   1.0050   0.02746   0.01744  -0.0092   0.1071   1.0000
   9.250   1.0176   0.02844   0.01841  -0.0074   0.1024   1.0000
   9.500   1.0327   0.02935   0.01942  -0.0059   0.0975   1.0000
   9.750   1.0462   0.03032   0.02043  -0.0043   0.0935   1.0000
  10.000   1.0597   0.03145   0.02153  -0.0029   0.0899   1.0000
  10.250   1.0751   0.03246   0.02271  -0.0016   0.0860   1.0000
  10.500   1.0893   0.03355   0.02388  -0.0002   0.0827   1.0000
  10.750   1.1029   0.03470   0.02506   0.0010   0.0800   1.0000
  11.000   1.1176   0.03601   0.02642   0.0022   0.0773   1.0000
  11.250   1.1309   0.03727   0.02788   0.0034   0.0743   1.0000
  11.500   1.1433   0.03858   0.02934   0.0047   0.0716   1.0000
  11.750   1.1550   0.03993   0.03075   0.0058   0.0695   1.0000
  12.000   1.1677   0.04136   0.03218   0.0068   0.0675   1.0000
  12.250   1.1773   0.04307   0.03411   0.0081   0.0655   1.0000
  12.500   1.1839   0.04487   0.03617   0.0094   0.0633   1.0000
  12.750   1.1904   0.04672   0.03822   0.0106   0.0616   1.0000
  13.000   1.1958   0.04858   0.04022   0.0117   0.0600   1.0000
  13.250   1.2017   0.05041   0.04213   0.0126   0.0585   1.0000
  13.500   1.2096   0.05227   0.04402   0.0134   0.0572   1.0000
  13.750   1.2076   0.05496   0.04695   0.0143   0.0559   1.0000
  14.000   1.2007   0.05810   0.05040   0.0150   0.0548   1.0000
  14.250   1.1926   0.06154   0.05412   0.0154   0.0538   1.0000
  14.500   1.1822   0.06533   0.05817   0.0154   0.0529   1.0000
  14.750   1.1699   0.06948   0.06255   0.0149   0.0522   1.0000
  15.000   1.1556   0.07402   0.06732   0.0139   0.0514   1.0000
  15.250   1.1378   0.07933   0.07285   0.0123   0.0510   1.0000
  15.500   1.1160   0.08558   0.07932   0.0097   0.0506   1.0000
  15.750   1.0837   0.09414   0.08813   0.0053   0.0505   1.0000
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