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NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NLR-1T AIRFOIL (nlr1t-il)
Reynolds number: 50,000
Max Cl/Cd: 28.28 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlr1t-il-50000-n5.txt
Download as CSV file: xf-nlr1t-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5273   0.11010   0.10313  -0.0132   1.0000   0.1253
  -9.250  -0.5256   0.10655   0.09963  -0.0144   1.0000   0.1297
  -9.000  -0.5612   0.10372   0.09698  -0.0231   1.0000   0.1350
  -8.750  -0.5291   0.09913   0.09235  -0.0174   1.0000   0.1397
  -8.500  -0.5472   0.08729   0.08039  -0.0308   1.0000   0.0627
  -8.250  -0.5464   0.08345   0.07657  -0.0307   1.0000   0.0612
  -8.000  -0.5492   0.07950   0.07263  -0.0311   1.0000   0.0599
  -7.750  -0.5532   0.07559   0.06869  -0.0312   1.0000   0.0586
  -7.500  -0.5576   0.07177   0.06480  -0.0307   1.0000   0.0573
  -7.250  -0.5622   0.06802   0.06093  -0.0296   1.0000   0.0559
  -6.750  -0.5742   0.06096   0.05296  -0.0249   1.0000   0.0509
  -6.500  -0.5687   0.05761   0.04952  -0.0228   1.0000   0.0504
  -6.250  -0.5628   0.05443   0.04621  -0.0206   1.0000   0.0498
  -6.000  -0.5561   0.05140   0.04297  -0.0183   1.0000   0.0491
  -5.750  -0.5478   0.04848   0.03976  -0.0160   1.0000   0.0485
  -5.500  -0.5376   0.04565   0.03657  -0.0136   1.0000   0.0480
  -5.250  -0.5254   0.04295   0.03350  -0.0114   1.0000   0.0475
  -5.000  -0.5110   0.04040   0.03057  -0.0093   1.0000   0.0472
  -4.750  -0.4945   0.03801   0.02779  -0.0073   1.0000   0.0470
  -4.500  -0.4759   0.03579   0.02517  -0.0055   1.0000   0.0470
  -4.250  -0.4555   0.03375   0.02275  -0.0039   1.0000   0.0473
  -4.000  -0.4337   0.03205   0.02064  -0.0025   1.0000   0.0489
  -3.750  -0.4108   0.03071   0.01886  -0.0010   1.0000   0.0510
  -3.500  -0.3873   0.02887   0.01694  -0.0003   1.0000   0.0533
  -3.250  -0.3624   0.02750   0.01544   0.0006   1.0000   0.0550
  -3.000  -0.3367   0.02632   0.01411   0.0015   1.0000   0.0570
  -2.750  -0.3109   0.02530   0.01292   0.0023   1.0000   0.0598
  -2.500  -0.2854   0.02446   0.01183   0.0031   1.0000   0.0634
  -2.250  -0.2617   0.02360   0.01092   0.0037   1.0000   0.0715
  -2.000  -0.1193   0.01897   0.00989  -0.0164   1.0000   1.0000
  -1.750  -0.1057   0.01894   0.00946  -0.0140   1.0000   1.0000
  -1.500  -0.0913   0.01892   0.00916  -0.0117   1.0000   1.0000
  -1.250  -0.0763   0.01894   0.00891  -0.0096   1.0000   1.0000
  -1.000  -0.0607   0.01897   0.00872  -0.0076   1.0000   1.0000
  -0.750  -0.0446   0.01903   0.00858  -0.0057   1.0000   1.0000
  -0.500  -0.0282   0.01912   0.00847  -0.0038   1.0000   1.0000
  -0.250  -0.0114   0.01922   0.00842  -0.0021   1.0000   1.0000
   0.000   0.0057   0.01934   0.00842  -0.0004   1.0000   1.0000
   0.250   0.0232   0.01949   0.00845   0.0012   1.0000   1.0000
   0.500   0.0409   0.01967   0.00852   0.0027   1.0000   1.0000
   0.750   0.0589   0.01986   0.00865   0.0041   1.0000   1.0000
   1.000   0.0770   0.02009   0.00882   0.0054   1.0000   1.0000
   1.250   0.0952   0.02035   0.00905   0.0066   1.0000   1.0000
   1.500   0.1570   0.02087   0.00957  -0.0009   0.9829   1.0000
   1.750   0.2451   0.02108   0.00986  -0.0129   0.9499   1.0000
   2.000   0.3210   0.02089   0.00981  -0.0218   0.9201   1.0000
   2.250   0.3719   0.02065   0.00971  -0.0257   0.8946   1.0000
   2.500   0.4099   0.02039   0.00960  -0.0268   0.8676   1.0000
   2.750   0.4390   0.02012   0.00946  -0.0261   0.8357   1.0000
   3.000   0.4560   0.01996   0.00944  -0.0232   0.7931   1.0000
   3.250   0.4690   0.01982   0.00940  -0.0196   0.7250   1.0000
   3.500   0.5331   0.01897   0.00789  -0.0225   0.5615   1.0000
   3.750   0.5517   0.01982   0.00804  -0.0200   0.4563   1.0000
   4.000   0.5685   0.02071   0.00852  -0.0179   0.3953   1.0000
   4.250   0.5883   0.02155   0.00913  -0.0165   0.3566   1.0000
   4.500   0.6098   0.02233   0.00975  -0.0154   0.3290   1.0000
   4.750   0.6327   0.02306   0.01040  -0.0145   0.3076   1.0000
   5.000   0.6568   0.02378   0.01110  -0.0139   0.2908   1.0000
   5.250   0.6820   0.02451   0.01189  -0.0134   0.2761   1.0000
   5.500   0.7075   0.02524   0.01268  -0.0130   0.2619   1.0000
   5.750   0.7329   0.02600   0.01351  -0.0125   0.2485   1.0000
   6.000   0.7569   0.02678   0.01437  -0.0119   0.2342   1.0000
   6.250   0.7779   0.02751   0.01514  -0.0109   0.2169   1.0000
   6.500   0.7976   0.02822   0.01592  -0.0097   0.1995   1.0000
   6.750   0.8180   0.02904   0.01680  -0.0086   0.1840   1.0000
   7.000   0.8384   0.02995   0.01779  -0.0075   0.1691   1.0000
   7.250   0.8573   0.03089   0.01892  -0.0062   0.1529   1.0000
   7.500   0.8767   0.03200   0.02015  -0.0050   0.1392   1.0000
   7.750   0.8967   0.03334   0.02170  -0.0038   0.1277   1.0000
   8.000   0.9160   0.03489   0.02355  -0.0026   0.1172   1.0000
   8.250   0.9337   0.03626   0.02511  -0.0012   0.1087   1.0000
   8.500   0.9506   0.03748   0.02648   0.0002   0.1016   1.0000
   8.750   0.9675   0.03949   0.02880   0.0016   0.0967   1.0000
   9.000   0.9827   0.04170   0.03138   0.0031   0.0926   1.0000
   9.250   0.9976   0.04361   0.03352   0.0046   0.0896   1.0000
   9.500   1.0108   0.04571   0.03580   0.0062   0.0869   1.0000
   9.750   1.0140   0.04908   0.03976   0.0086   0.0838   1.0000
  10.000   1.0164   0.05191   0.04297   0.0108   0.0806   1.0000
  10.250   1.0212   0.05417   0.04546   0.0129   0.0779   1.0000
  10.500   1.0253   0.05667   0.04814   0.0148   0.0762   1.0000
  10.750   1.0253   0.05967   0.05129   0.0168   0.0750   1.0000
  11.000   1.0061   0.06406   0.05606   0.0195   0.0746   1.0000
  11.250   0.9811   0.06838   0.06062   0.0222   0.0745   1.0000
  11.500   0.9533   0.07344   0.06586   0.0231   0.0745   1.0000
  11.750   0.9233   0.07967   0.07222   0.0218   0.0747   1.0000
  12.000   0.8920   0.08757   0.08018   0.0178   0.0750   1.0000
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