Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(3)-618 (naca633618-il)
Reynolds number: 100,000
Max Cl/Cd: 46.46 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca633618-il-100000-n5.txt
Download as CSV file: xf-naca633618-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(3)-618                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.5632   0.08488   0.07899  -0.0798   1.0000   0.0446
 -14.250  -0.6130   0.07427   0.06813  -0.0864   1.0000   0.0442
 -14.000  -0.6445   0.06764   0.06130  -0.0898   1.0000   0.0443
 -13.750  -0.6690   0.06255   0.05602  -0.0917   1.0000   0.0445
 -13.500  -0.6897   0.05839   0.05166  -0.0926   1.0000   0.0449
 -13.250  -0.7091   0.05483   0.04790  -0.0927   1.0000   0.0454
 -13.000  -0.7269   0.05192   0.04481  -0.0919   1.0000   0.0459
 -12.750  -0.7410   0.04991   0.04272  -0.0900   1.0000   0.0465
 -12.500  -0.7517   0.04884   0.04169  -0.0870   1.0000   0.0470
 -12.250  -0.7399   0.04707   0.03988  -0.0884   0.9929   0.0482
 -12.000  -0.7224   0.04469   0.03731  -0.0914   0.9827   0.0499
 -11.750  -0.7070   0.04220   0.03452  -0.0940   0.9717   0.0517
 -11.500  -0.6866   0.04020   0.03234  -0.0961   0.9622   0.0535
 -11.250  -0.6586   0.03863   0.03072  -0.0987   0.9557   0.0555
 -11.000  -0.6368   0.03705   0.02896  -0.1002   0.9458   0.0578
 -10.750  -0.6091   0.03534   0.02700  -0.1025   0.9394   0.0603
 -10.500  -0.5847   0.03420   0.02590  -0.1033   0.9297   0.0624
 -10.250  -0.5559   0.03291   0.02449  -0.1051   0.9232   0.0653
 -10.000  -0.5342   0.03183   0.02320  -0.1053   0.9131   0.0679
  -9.750  -0.5057   0.03072   0.02214  -0.1064   0.9066   0.0705
  -9.500  -0.4860   0.02986   0.02124  -0.1061   0.8967   0.0732
  -9.250  -0.4615   0.02897   0.02019  -0.1064   0.8892   0.0767
  -9.000  -0.4440   0.02814   0.01940  -0.1058   0.8797   0.0795
  -8.750  -0.4234   0.02732   0.01854  -0.1056   0.8716   0.0830
  -8.500  -0.4056   0.02666   0.01777  -0.1048   0.8628   0.0871
  -8.250  -0.3892   0.02585   0.01700  -0.1041   0.8544   0.0915
  -8.000  -0.3711   0.02517   0.01625  -0.1034   0.8469   0.0974
  -7.750  -0.3564   0.02445   0.01555  -0.1023   0.8381   0.1035
  -7.500  -0.3358   0.02371   0.01475  -0.1020   0.8321   0.1131
  -7.250  -0.3212   0.02308   0.01415  -0.1008   0.8233   0.1250
  -7.000  -0.3024   0.02231   0.01342  -0.1003   0.8164   0.1423
  -6.750  -0.2831   0.02151   0.01271  -0.1000   0.8102   0.1677
  -6.500  -0.2661   0.02076   0.01212  -0.0994   0.8023   0.2022
  -6.250  -0.2448   0.01989   0.01147  -0.0994   0.7965   0.2552
  -6.000  -0.2233   0.01924   0.01112  -0.0993   0.7903   0.3170
  -5.750  -0.2008   0.01898   0.01109  -0.0988   0.7832   0.3741
  -5.500  -0.1735   0.01888   0.01100  -0.0988   0.7779   0.4171
  -5.250  -0.1461   0.01888   0.01093  -0.0988   0.7726   0.4492
  -5.000  -0.1215   0.01904   0.01109  -0.0981   0.7656   0.4724
  -4.750  -0.0937   0.01915   0.01113  -0.0979   0.7602   0.4930
  -4.500  -0.0644   0.01926   0.01112  -0.0978   0.7560   0.5104
  -4.250  -0.0403   0.01941   0.01121  -0.0973   0.7488   0.5245
  -4.000  -0.0131   0.01951   0.01124  -0.0969   0.7432   0.5366
  -3.750   0.0155   0.01962   0.01126  -0.0966   0.7389   0.5475
  -3.500   0.0413   0.01971   0.01126  -0.0965   0.7326   0.5601
  -3.250   0.0663   0.01991   0.01145  -0.0955   0.7268   0.5679
  -3.000   0.0964   0.01978   0.01115  -0.0962   0.7222   0.5776
  -2.750   0.1233   0.01984   0.01118  -0.0957   0.7175   0.5828
  -2.500   0.1479   0.01993   0.01124  -0.0952   0.7110   0.5893
  -2.250   0.1772   0.01983   0.01101  -0.0958   0.7060   0.5975
  -2.000   0.2055   0.01984   0.01097  -0.0956   0.7022   0.6022
  -1.750   0.2305   0.01993   0.01105  -0.0952   0.6963   0.6082
  -1.500   0.2587   0.01989   0.01090  -0.0958   0.6905   0.6161
  -1.250   0.2860   0.01991   0.01090  -0.0954   0.6862   0.6203
  -1.000   0.3155   0.01989   0.01081  -0.0956   0.6827   0.6256
  -0.750   0.3397   0.02002   0.01094  -0.0954   0.6762   0.6322
  -0.500   0.3670   0.02004   0.01093  -0.0955   0.6711   0.6376
  -0.250   0.3954   0.02004   0.01089  -0.0954   0.6671   0.6421
   0.000   0.4231   0.02009   0.01092  -0.0955   0.6627   0.6479
   0.250   0.4492   0.02023   0.01104  -0.0958   0.6569   0.6549
   0.500   0.4749   0.02031   0.01115  -0.0953   0.6523   0.6590
   0.750   0.5041   0.02031   0.01112  -0.0955   0.6486   0.6640
   1.000   0.5311   0.02043   0.01122  -0.0957   0.6438   0.6704
   1.250   0.5553   0.02062   0.01146  -0.0954   0.6381   0.6762
   1.500   0.5815   0.02073   0.01160  -0.0951   0.6339   0.6812
   1.750   0.6116   0.02075   0.01158  -0.0955   0.6304   0.6873
   2.000   0.6378   0.02094   0.01179  -0.0957   0.6254   0.6939
   2.250   0.6594   0.02119   0.01213  -0.0947   0.6198   0.6987
   2.500   0.6863   0.02131   0.01228  -0.0946   0.6156   0.7051
   2.750   0.7181   0.02133   0.01226  -0.0955   0.6122   0.7124
   3.000   0.7387   0.02163   0.01267  -0.0944   0.6069   0.7174
   3.250   0.7613   0.02190   0.01303  -0.0937   0.6014   0.7237
   3.500   0.7904   0.02201   0.01314  -0.0942   0.5972   0.7313
   3.750   0.8192   0.02202   0.01317  -0.0941   0.5938   0.7369
   4.000   0.8374   0.02247   0.01376  -0.0929   0.5875   0.7441
   4.250   0.8617   0.02271   0.01407  -0.0926   0.5822   0.7512
   4.500   0.8890   0.02276   0.01416  -0.0924   0.5781   0.7577
   4.750   0.9163   0.02293   0.01438  -0.0925   0.5738   0.7658
   5.000   0.9319   0.02340   0.01501  -0.0908   0.5672   0.7726
   5.250   0.9574   0.02355   0.01522  -0.0905   0.5624   0.7804
   5.500   0.9893   0.02352   0.01521  -0.0911   0.5586   0.7883
   5.750   1.0012   0.02410   0.01597  -0.0888   0.5517   0.7964
   6.000   1.0245   0.02433   0.01628  -0.0883   0.5459   0.8052
   6.250   1.0540   0.02422   0.01622  -0.0883   0.5415   0.8132
   6.500   1.0663   0.02479   0.01695  -0.0863   0.5340   0.8231
   6.750   1.0870   0.02489   0.01715  -0.0850   0.5275   0.8325
   7.000   1.1138   0.02482   0.01713  -0.0846   0.5214   0.8423
   7.250   1.1219   0.02532   0.01780  -0.0818   0.5125   0.8542
   7.500   1.1508   0.02499   0.01749  -0.0815   0.5062   0.8650
   7.750   1.1502   0.02565   0.01835  -0.0774   0.4969   0.8799
   8.000   1.1742   0.02541   0.01816  -0.0763   0.4896   0.8948
   8.250   1.1704   0.02602   0.01894  -0.0718   0.4804   0.9198
   8.500   1.1949   0.02572   0.01870  -0.0710   0.4719   0.9573
   8.750   1.2001   0.02667   0.01979  -0.0691   0.4605   1.0000
   9.000   1.2183   0.02716   0.02032  -0.0685   0.4496   1.0000
   9.250   1.2382   0.02751   0.02068  -0.0679   0.4379   1.0000
   9.500   1.2414   0.02877   0.02204  -0.0660   0.4244   1.0000
   9.750   1.2482   0.02988   0.02321  -0.0645   0.4098   1.0000
  10.000   1.2537   0.03111   0.02445  -0.0629   0.3932   1.0000
  10.250   1.2577   0.03251   0.02583  -0.0613   0.3745   1.0000
  10.500   1.2614   0.03400   0.02727  -0.0598   0.3537   1.0000
  10.750   1.2617   0.03592   0.02915  -0.0584   0.3316   1.0000
  11.000   1.2627   0.03785   0.03097  -0.0570   0.3086   1.0000
  11.250   1.2625   0.04001   0.03303  -0.0558   0.2866   1.0000
  11.500   1.2606   0.04245   0.03539  -0.0547   0.2649   1.0000
  11.750   1.2578   0.04508   0.03794  -0.0538   0.2443   1.0000
  12.000   1.2543   0.04790   0.04067  -0.0530   0.2254   1.0000
  12.250   1.2513   0.05084   0.04355  -0.0524   0.2075   1.0000
  12.500   1.2484   0.05389   0.04655  -0.0520   0.1908   1.0000
  12.750   1.2458   0.05702   0.04965  -0.0518   0.1754   1.0000
  13.000   1.2432   0.06027   0.05286  -0.0517   0.1609   1.0000
  13.250   1.2408   0.06360   0.05615  -0.0518   0.1477   1.0000
  13.500   1.2387   0.06699   0.05952  -0.0520   0.1354   1.0000
  13.750   1.2380   0.07033   0.06287  -0.0523   0.1240   1.0000
  14.000   1.2372   0.07371   0.06627  -0.0526   0.1138   1.0000
  14.250   1.2360   0.07724   0.06980  -0.0531   0.1049   1.0000
  14.500   1.2344   0.08088   0.07343  -0.0537   0.0972   1.0000
  14.750   1.2357   0.08420   0.07681  -0.0543   0.0900   1.0000
  15.000   1.2349   0.08782   0.08041  -0.0550   0.0846   1.0000
  15.250   1.2371   0.09109   0.08376  -0.0557   0.0790   1.0000
  15.500   1.2372   0.09466   0.08730  -0.0566   0.0750   1.0000
  15.750   1.2411   0.09775   0.09049  -0.0573   0.0706   1.0000
<< Back to NACA 63(3)-618 (naca633618-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(3)-618 (naca633618-il)