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

NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA NLF1015 (nlf1015-il)
Reynolds number: 500,000
Max Cl/Cd: 125.85 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf1015-il-500000-n5.txt
Download as CSV file: xf-nlf1015-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA  NLF1015                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2369   0.04034   0.03693  -0.1754   0.9076   0.0098
 -11.000  -0.2412   0.03506   0.03126  -0.1820   0.8919   0.0097
 -10.750  -0.2435   0.03220   0.02814  -0.1837   0.8776   0.0098
 -10.500  -0.2518   0.02961   0.02525  -0.1829   0.8643   0.0098
 -10.250  -0.2588   0.02790   0.02332  -0.1806   0.8527   0.0098
 -10.000  -0.2606   0.02645   0.02167  -0.1784   0.8438   0.0099
  -9.750  -0.2550   0.02489   0.01986  -0.1770   0.8366   0.0099
  -9.500  -0.2458   0.02351   0.01827  -0.1756   0.8306   0.0100
  -9.250  -0.2323   0.02241   0.01700  -0.1746   0.8249   0.0102
  -9.000  -0.2164   0.02123   0.01560  -0.1738   0.8203   0.0103
  -8.750  -0.1998   0.02020   0.01441  -0.1729   0.8156   0.0104
  -8.500  -0.1812   0.01927   0.01333  -0.1722   0.8110   0.0106
  -8.250  -0.1607   0.01841   0.01230  -0.1717   0.8069   0.0108
  -8.000  -0.1399   0.01763   0.01139  -0.1711   0.8030   0.0110
  -7.750  -0.1187   0.01691   0.01056  -0.1706   0.7990   0.0113
  -7.500  -0.0963   0.01626   0.00980  -0.1702   0.7954   0.0116
  -7.250  -0.0730   0.01564   0.00906  -0.1699   0.7922   0.0118
  -7.000  -0.0495   0.01508   0.00842  -0.1697   0.7893   0.0120
  -6.750  -0.0261   0.01458   0.00785  -0.1694   0.7861   0.0122
  -6.500  -0.0018   0.01414   0.00734  -0.1692   0.7830   0.0124
  -6.250   0.0230   0.01370   0.00684  -0.1692   0.7801   0.0127
  -6.000   0.0473   0.01303   0.00609  -0.1693   0.7773   0.0134
  -5.750   0.0730   0.01260   0.00563  -0.1694   0.7747   0.0138
  -5.500   0.0987   0.01222   0.00521  -0.1695   0.7718   0.0143
  -5.250   0.1253   0.01190   0.00484  -0.1697   0.7691   0.0147
  -5.000   0.1525   0.01161   0.00450  -0.1700   0.7667   0.0153
  -4.750   0.1803   0.01137   0.00419  -0.1704   0.7644   0.0161
  -4.500   0.2087   0.01117   0.00392  -0.1709   0.7624   0.0167
  -4.250   0.2370   0.01096   0.00367  -0.1714   0.7604   0.0178
  -4.000   0.2646   0.01076   0.00345  -0.1717   0.7581   0.0201
  -3.750   0.2926   0.01051   0.00326  -0.1722   0.7556   0.0306
  -3.500   0.3213   0.01013   0.00306  -0.1729   0.7532   0.0793
  -3.250   0.3506   0.00979   0.00290  -0.1739   0.7511   0.1349
  -3.000   0.3806   0.00947   0.00277  -0.1750   0.7492   0.2008
  -2.750   0.4117   0.00911   0.00265  -0.1764   0.7475   0.2833
  -2.500   0.4439   0.00864   0.00252  -0.1782   0.7458   0.3987
  -2.250   0.4757   0.00820   0.00262  -0.1798   0.7439   0.5655
  -2.000   0.5043   0.00822   0.00268  -0.1802   0.7417   0.5950
  -1.750   0.5329   0.00826   0.00270  -0.1805   0.7395   0.6084
  -1.500   0.5618   0.00831   0.00272  -0.1809   0.7376   0.6203
  -1.250   0.5907   0.00835   0.00276  -0.1813   0.7358   0.6288
  -1.000   0.6200   0.00841   0.00277  -0.1818   0.7340   0.6367
  -0.750   0.6494   0.00847   0.00281  -0.1823   0.7322   0.6439
  -0.500   0.6780   0.00853   0.00285  -0.1827   0.7303   0.6513
  -0.250   0.7055   0.00858   0.00293  -0.1828   0.7283   0.6573
   0.000   0.7336   0.00863   0.00298  -0.1830   0.7262   0.6635
   0.250   0.7616   0.00868   0.00304  -0.1833   0.7240   0.6684
   0.500   0.7896   0.00873   0.00311  -0.1835   0.7219   0.6731
   0.750   0.8183   0.00880   0.00315  -0.1839   0.7197   0.6778
   1.000   0.8478   0.00887   0.00319  -0.1844   0.7175   0.6814
   1.250   0.8747   0.00891   0.00327  -0.1844   0.7148   0.6841
   1.500   0.9008   0.00895   0.00335  -0.1843   0.7114   0.6866
   1.750   0.9274   0.00899   0.00341  -0.1842   0.7078   0.6893
   2.000   0.9551   0.00904   0.00346  -0.1844   0.7043   0.6923
   2.250   0.9824   0.00911   0.00353  -0.1845   0.7007   0.6952
   2.750   1.0330   0.00919   0.00370  -0.1838   0.6917   0.7003
   3.000   1.0603   0.00926   0.00376  -0.1839   0.6876   0.7030
   3.250   1.0842   0.00931   0.00388  -0.1833   0.6827   0.7061
   3.500   1.1089   0.00937   0.00397  -0.1828   0.6773   0.7091
   3.750   1.1343   0.00945   0.00406  -0.1825   0.6719   0.7121
   4.000   1.1569   0.00950   0.00419  -0.1816   0.6649   0.7148
   4.250   1.1803   0.00958   0.00428  -0.1808   0.6581   0.7177
   4.500   1.2020   0.00966   0.00443  -0.1797   0.6500   0.7211
   4.750   1.2228   0.00975   0.00456  -0.1784   0.6412   0.7249
   5.000   1.2409   0.00986   0.00468  -0.1765   0.6300   0.7286
   5.250   1.2552   0.01001   0.00484  -0.1738   0.6126   0.7317
   5.500   1.2639   0.01032   0.00507  -0.1700   0.5829   0.7354
   5.750   1.2667   0.01088   0.00547  -0.1652   0.5442   0.7397
   6.250   1.2607   0.01272   0.00688  -0.1538   0.4549   0.7484
   6.500   1.2592   0.01377   0.00774  -0.1488   0.4132   0.7534
   6.750   1.2572   0.01496   0.00873  -0.1440   0.3703   0.7586
   7.000   1.2508   0.01646   0.00996  -0.1387   0.3188   0.7634
   7.250   1.2497   0.01785   0.01115  -0.1345   0.2748   0.7687
   7.500   1.2483   0.01940   0.01245  -0.1306   0.2290   0.7742
   7.750   1.2543   0.02059   0.01354  -0.1278   0.1989   0.7793
   8.000   1.2612   0.02181   0.01465  -0.1253   0.1713   0.7853
   8.500   1.2763   0.02429   0.01694  -0.1206   0.1210   0.7980
   9.000   1.2874   0.02723   0.01964  -0.1159   0.0678   0.8123
   9.500   1.2989   0.03036   0.02259  -0.1115   0.0259   0.8281
   9.750   1.3051   0.03197   0.02414  -0.1095   0.0119   0.8367
  10.000   1.3163   0.03317   0.02539  -0.1080   0.0098   0.8467
  10.250   1.3281   0.03432   0.02663  -0.1066   0.0087   0.8580
  10.500   1.3397   0.03547   0.02788  -0.1051   0.0081   0.8718
  10.750   1.3503   0.03663   0.02915  -0.1035   0.0077   0.8909
  11.000   1.3559   0.03765   0.03032  -0.1009   0.0073   0.9419
  11.250   1.3654   0.03897   0.03172  -0.0995   0.0070   1.0000
  11.500   1.3757   0.04053   0.03335  -0.0984   0.0067   1.0000
  11.750   1.3849   0.04222   0.03511  -0.0973   0.0064   1.0000
  12.000   1.3959   0.04377   0.03673  -0.0963   0.0063   1.0000
  12.250   1.4059   0.04541   0.03846  -0.0954   0.0061   1.0000
  12.500   1.4155   0.04712   0.04024  -0.0944   0.0059   1.0000
  12.750   1.4242   0.04896   0.04217  -0.0935   0.0057   1.0000
  13.000   1.4326   0.05086   0.04415  -0.0926   0.0056   1.0000
  13.250   1.4400   0.05290   0.04627  -0.0918   0.0054   1.0000
  13.500   1.4465   0.05507   0.04852  -0.0909   0.0053   1.0000
  13.750   1.4521   0.05737   0.05091  -0.0901   0.0051   1.0000
  14.000   1.4570   0.05979   0.05343  -0.0894   0.0050   1.0000
  14.250   1.4614   0.06234   0.05606  -0.0887   0.0049   1.0000
  14.500   1.4647   0.06507   0.05888  -0.0881   0.0049   1.0000
  14.750   1.4673   0.06794   0.06185  -0.0876   0.0048   1.0000
  15.000   1.4688   0.07099   0.06501  -0.0872   0.0047   1.0000
  15.250   1.4689   0.07428   0.06841  -0.0869   0.0046   1.0000
  15.500   1.4682   0.07779   0.07202  -0.0867   0.0045   1.0000
  15.750   1.4660   0.08155   0.07589  -0.0866   0.0045   1.0000
  16.000   1.4631   0.08550   0.07995  -0.0867   0.0044   1.0000
<< Back to NASA NLF1015 (nlf1015-il)

Polar data table (+)

Polar graphs


<< Back to NASA NLF1015 (nlf1015-il)