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NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NLR-1T AIRFOIL (nlr1t-il)
Reynolds number: 100,000
Max Cl/Cd: 39.51 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlr1t-il-100000-n5.txt
Download as CSV file: xf-nlr1t-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-1T 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5269   0.09033   0.08549  -0.0232   1.0000   0.0581
  -8.500  -0.5318   0.08574   0.08095  -0.0270   1.0000   0.0589
  -8.250  -0.5403   0.08144   0.07668  -0.0297   1.0000   0.0595
  -8.000  -0.5473   0.07736   0.07259  -0.0312   1.0000   0.0602
  -7.750  -0.5805   0.07545   0.07028  -0.0321   1.0000   0.0640
  -7.500  -0.5218   0.05604   0.05132  -0.0314   1.0000   0.0374
  -7.250  -0.5740   0.06275   0.05754  -0.0284   1.0000   0.0368
  -7.000  -0.5780   0.05969   0.05441  -0.0256   1.0000   0.0353
  -6.750  -0.5812   0.05636   0.05092  -0.0227   1.0000   0.0337
  -6.250  -0.5805   0.04822   0.04177  -0.0154   1.0000   0.0283
  -6.000  -0.5746   0.04502   0.03838  -0.0129   1.0000   0.0279
  -5.750  -0.5665   0.04210   0.03520  -0.0104   1.0000   0.0276
  -5.500  -0.5561   0.03933   0.03212  -0.0080   1.0000   0.0274
  -5.250  -0.5434   0.03673   0.02917  -0.0056   1.0000   0.0273
  -5.000  -0.5280   0.03465   0.02661  -0.0033   1.0000   0.0280
  -4.750  -0.5122   0.03230   0.02385  -0.0013   1.0000   0.0290
  -4.500  -0.4942   0.03014   0.02143   0.0002   1.0000   0.0297
  -4.250  -0.4735   0.02830   0.01923   0.0017   1.0000   0.0296
  -4.000  -0.4515   0.02663   0.01727   0.0030   1.0000   0.0296
  -3.750  -0.4285   0.02511   0.01552   0.0041   1.0000   0.0298
  -3.500  -0.4026   0.02374   0.01394   0.0046   0.9994   0.0302
  -3.250  -0.3750   0.02254   0.01260   0.0047   0.9984   0.0308
  -3.000  -0.3456   0.02148   0.01145   0.0044   0.9967   0.0316
  -2.750  -0.3149   0.02056   0.01048   0.0038   0.9948   0.0329
  -2.500  -0.2856   0.01990   0.00975   0.0034   0.9924   0.0361
  -2.250  -0.2572   0.01930   0.00906   0.0033   0.9900   0.0391
  -2.000  -0.2289   0.01859   0.00830   0.0030   0.9879   0.0422
  -1.750  -0.1981   0.01816   0.00778   0.0023   0.9857   0.0473
  -1.500  -0.1684   0.01768   0.00729   0.0019   0.9829   0.0598
  -1.250  -0.0730   0.01484   0.00787  -0.0107   0.9965   1.0000
  -1.000  -0.0404   0.01491   0.00771  -0.0121   0.9926   1.0000
  -0.750  -0.0066   0.01499   0.00760  -0.0137   0.9879   1.0000
  -0.500   0.0295   0.01509   0.00755  -0.0158   0.9832   1.0000
  -0.250   0.0672   0.01517   0.00751  -0.0182   0.9769   1.0000
   0.000   0.1161   0.01518   0.00741  -0.0227   0.9670   1.0000
   0.250   0.2212   0.01451   0.00664  -0.0375   0.9391   1.0000
   0.500   0.2744   0.01407   0.00614  -0.0419   0.9192   1.0000
   0.750   0.3034   0.01398   0.00604  -0.0419   0.9070   1.0000
   1.000   0.3307   0.01390   0.00596  -0.0415   0.8944   1.0000
   1.250   0.3568   0.01380   0.00587  -0.0407   0.8800   1.0000
   1.500   0.3817   0.01368   0.00575  -0.0396   0.8629   1.0000
   1.750   0.4033   0.01358   0.00568  -0.0379   0.8411   1.0000
   2.000   0.4243   0.01348   0.00562  -0.0360   0.8131   1.0000
   2.250   0.4410   0.01347   0.00565  -0.0335   0.7648   1.0000
   2.500   0.4731   0.01302   0.00463  -0.0321   0.6305   1.0000
   2.750   0.4926   0.01364   0.00457  -0.0298   0.5049   1.0000
   3.000   0.5115   0.01435   0.00482  -0.0281   0.4133   1.0000
   3.250   0.5319   0.01497   0.00509  -0.0268   0.3487   1.0000
   3.500   0.5534   0.01551   0.00538  -0.0257   0.3062   1.0000
   3.750   0.5754   0.01600   0.00571  -0.0247   0.2786   1.0000
   4.000   0.5977   0.01645   0.00610  -0.0237   0.2603   1.0000
   4.250   0.6200   0.01690   0.00649  -0.0228   0.2463   1.0000
   4.500   0.6425   0.01735   0.00690  -0.0218   0.2348   1.0000
   4.750   0.6647   0.01783   0.00733  -0.0209   0.2252   1.0000
   5.000   0.6871   0.01827   0.00778  -0.0199   0.2149   1.0000
   5.250   0.7094   0.01871   0.00827  -0.0190   0.2036   1.0000
   5.500   0.7314   0.01914   0.00871  -0.0181   0.1913   1.0000
   5.750   0.7531   0.01957   0.00914  -0.0171   0.1789   1.0000
   6.000   0.7746   0.02002   0.00960  -0.0161   0.1682   1.0000
   6.250   0.7965   0.02043   0.01014  -0.0152   0.1571   1.0000
   6.500   0.8183   0.02089   0.01071  -0.0142   0.1466   1.0000
   6.750   0.8395   0.02136   0.01127  -0.0131   0.1344   1.0000
   7.000   0.8606   0.02182   0.01182  -0.0120   0.1196   1.0000
   7.250   0.8815   0.02231   0.01239  -0.0109   0.1035   1.0000
   7.500   0.9016   0.02295   0.01308  -0.0097   0.0914   1.0000
   7.750   0.9206   0.02376   0.01391  -0.0083   0.0831   1.0000
   8.000   0.9390   0.02464   0.01482  -0.0069   0.0771   1.0000
   8.250   0.9569   0.02566   0.01592  -0.0054   0.0727   1.0000
   8.500   0.9752   0.02666   0.01707  -0.0039   0.0685   1.0000
   8.750   0.9923   0.02767   0.01815  -0.0024   0.0649   1.0000
   9.000   1.0087   0.02891   0.01951  -0.0009   0.0621   1.0000
   9.250   1.0263   0.03019   0.02103   0.0006   0.0600   1.0000
   9.500   1.0430   0.03158   0.02265   0.0022   0.0580   1.0000
   9.750   1.0589   0.03304   0.02433   0.0038   0.0563   1.0000
  10.000   1.0737   0.03455   0.02601   0.0054   0.0545   1.0000
  10.250   1.0873   0.03609   0.02765   0.0070   0.0526   1.0000
  10.500   1.0983   0.03810   0.02988   0.0089   0.0507   1.0000
  10.750   1.1066   0.04011   0.03235   0.0112   0.0489   1.0000
  11.000   1.1117   0.04204   0.03464   0.0137   0.0465   1.0000
  11.250   1.1175   0.04309   0.03581   0.0159   0.0433   1.0000
  11.500   1.1206   0.04458   0.03722   0.0181   0.0403   1.0000
  11.750   1.1129   0.04636   0.03944   0.0218   0.0381   1.0000
  12.000   1.1048   0.04858   0.04198   0.0247   0.0360   1.0000
  12.250   1.0971   0.05098   0.04461   0.0269   0.0343   1.0000
  12.500   1.0903   0.05336   0.04714   0.0284   0.0328   1.0000
  12.750   1.0847   0.05577   0.04961   0.0293   0.0314   1.0000
  13.250   1.0539   0.06443   0.05860   0.0284   0.0300   1.0000
  13.500   1.0325   0.07078   0.06519   0.0254   0.0300   1.0000
  13.750   1.0098   0.07846   0.07306   0.0206   0.0302   1.0000
  14.000   0.8886   0.11217   0.10710  -0.0003   0.0403   1.0000
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