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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)

NASA/LANGLEY NLF(2)-0415 AIRFOIL - NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil


Airfoil nlf415-il
Details Dat file Parser  
(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL
NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil
Max thickness 15% at 47.1% chord.
Max camber 3% at 71.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/LANGLEY NLF(2)-0415 AIRFOIL
      67.0      65.0

 0.0000283 0.0001977
 0.0001580 0.0018782
 0.0005781 0.0034513
 0.0012354 0.0049151
 0.0020767 0.0062942
 0.0030483 0.0076132
 0.0048657 0.0097598
 0.0072362 0.0121647
 0.0097802 0.0143864
 0.0126772 0.0165900
 0.0161151 0.0188727
 0.0196734 0.0209524
 0.0233271 0.0228708
 0.0284762 0.0253213
 0.0344332 0.0278754
 0.0404768 0.0302213
 0.0481623 0.0329347
 0.0567129 0.0356738
 0.0653312 0.0381994
 0.0770819 0.0413574
 0.0888958 0.0442664
 0.1034498 0.0475683
 0.1194057 0.0509036
 0.1366659 0.0542431
 0.1545967 0.0574695
 0.1762957 0.0610990
 0.1999052 0.0647528
 0.2252574 0.0683730
 0.2511119 0.0717686
 0.2779291 0.0749936
 0.3054984 0.0780026
 0.3334588 0.0807457
 0.3622074 0.0832480
 0.3911308 0.0854336
 0.4203734 0.0872973
 0.4464551 0.0886623
 0.4709578 0.0896782
 0.4953701 0.0904177
 0.5197378 0.0908721
 0.5438408 0.0910307
 0.5678078 0.0908768
 0.5891203 0.0904519
 0.6090986 0.0897875
 0.6280169 0.0889052
 0.6448200 0.0878954
 0.6616064 0.0866422
 0.6757030 0.0853765
 0.6884416 0.0840321
 0.7011539 0.0824596
 0.7141083 0.0805784
 0.7275568 0.0783021
 0.7409475 0.0757130
 0.7541982 0.0728412
 0.7672220 0.0697441
 0.7801957 0.0664444
 0.7964010 0.0621125
 0.8190836 0.0557941
 0.8505346 0.0467394
 0.8955132 0.0334861
 0.9249468 0.0247040
 0.9399937 0.0201262
 0.9540721 0.0156569
 0.9662560 0.0115595
 0.9781089 0.0073526
 0.9879752 0.0038258
 0.9941875 0.0017348
 1.0000000 0.0000000

 0.0000283 0.0001977
 0.0002160 -.0014055
 0.0007030 -.0029037
 0.0014684 -.0043042
 0.0025414 -.0056681
 0.0039070 -.0069317
 0.0054110 -.0079697
 0.0070198 -.0088373
 0.0086994 -.0095897
 0.0104158 -.0102821
 0.0165490 -.0126481
 0.0227369 -.0148649
 0.0291896 -.0169172
 0.0358008 -.0187691
 0.0424562 -.0204598
 0.0546129 -.0233186
 0.0695675 -.0265412
 0.0842934 -.0294302
 0.0990596 -.0321051
 0.1192222 -.0354972
 0.1401296 -.0387463
 0.1624827 -.0419577
 0.1860574 -.0450866
 0.2102588 -.0480371
 0.2359435 -.0508779
 0.2620312 -.0534583
 0.2888914 -.0557890
 0.3132250 -.0576002
 0.3363004 -.0590362
 0.3574037 -.0600921
 0.3775230 -.0608539
 0.3968363 -.0613459
 0.4145228 -.0615713
 0.4322107 -.0615507
 0.4474670 -.0613098
 0.4614996 -.0608672
 0.4755211 -.0601643
 0.4895594 -.0591512
 0.5036273 -.0578040
 0.5176603 -.0561485
 0.5316613 -.0542105
 0.5478030 -.0516619
 0.5639025 -.0488660
 0.5799760 -.0459166
 0.6175163 -.0388157
 0.6503252 -.0326355
 0.6807982 -.0270767
 0.7059723 -.0226781
 0.7311841 -.0185007
 0.7556095 -.0147144
 0.7800767 -.0112075
 0.8032020 -.0081807
 0.8263655 -.0054618
 0.8476593 -.0032672
 0.8689834 -.0013869
 0.8879449 -.0000039
 0.9069262 0.0010752
 0.9231043 0.0017266
 0.9392914 0.0021036
 0.9522953 0.0021864
 0.9652988 0.0020429
 0.9767429 0.0016978
 0.9867086 0.0011870
 0.9937244 0.0006571
 1.0000000 0.0000000
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Polars for NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nlf415-il50,000923.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf415-il50,000521.1 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf415-il100,000927.2 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf415-il100,000528.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf415-il200,000936.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf415-il200,000545.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf415-il500,000985.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf415-il500,000582.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf415-il1,000,0009118.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf415-il1,000,0005107.5 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
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