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NASA/LANGLEY RC-08(N)1 AIRFOIL (rc08n1-il)

NASA/LANGLEY RC-08(N)1 AIRFOIL - NASA/Langley RC-08(N)1 rotorcraft airfoil


Airfoil rc08n1-il
Details Dat file Parser  
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL
NASA/Langley RC-08(N)1 rotorcraft airfoil
Max thickness 8% at 37.5% chord.
Max camber 1.6% at 25% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/LANGLEY RC-08(N)1 AIRFOIL
       42.       42.

 0.0000000 0.0000000
 0.0008066 0.0029636
 0.0033513 0.0064148
 0.0097188 0.0115330
 0.0232280 0.0185026
 0.0480010 0.0268719
 0.0734842 0.0329343
 0.0985637 0.0375750
 0.1236869 0.0413658
 0.1488723 0.0446069
 0.1740903 0.0473181
 0.1993904 0.0495497
 0.2246423 0.0513410
 0.2498059 0.0527219
 0.3000980 0.0544737
 0.3503653 0.0550354
 0.3754958 0.0548964
 0.4005975 0.0544869
 0.4257005 0.0537777
 0.4508049 0.0527784
 0.4758805 0.0514689
 0.5009274 0.0498794
 0.5259755 0.0480199
 0.5510147 0.0459203
 0.5760248 0.0436005
 0.6010560 0.0410508
 0.6260980 0.0382914
 0.6511309 0.0353418
 0.6761745 0.0322322
 0.7011386 0.0290123
 0.7260129 0.0257519
 0.7509668 0.0225419
 0.7758303 0.0194616
 0.8005429 0.0165906
 0.8253245 0.0139198
 0.8501654 0.0114493
 0.8750453 0.0091590
 0.8999946 0.0070490
 0.9249730 0.0051291
 0.9499404 0.0033993
 0.9749169 0.0018794
 1.0000000 0.0006400

 0.0000000 0.0000000
 0.0042010 -.0048315
 0.0066447 -.0056907
 0.0152585 -.0065428
 0.0267273 -.0085722
 0.0519256 -.0104911
 0.0764230 -.0121730
 0.1013303 -.0138332
 0.1261871 -.0154137
 0.1509934 -.0168543
 0.1757692 -.0181750
 0.2004644 -.0193960
 0.2252092 -.0205270
 0.2500437 -.0215874
 0.2997415 -.0233983
 0.3494774 -.0247589
 0.3743493 -.0252493
 0.3992507 -.0255995
 0.4241616 -.0257997
 0.4490515 -.0258299
 0.4739807 -.0256800
 0.4989293 -.0253599
 0.5238969 -.0248698
 0.5488642 -.0242397
 0.5738507 -.0234796
 0.5988268 -.0226193
 0.6237926 -.0217092
 0.6487683 -.0207691
 0.6737344 -.0198590
 0.6987806 -.0190185
 0.7239169 -.0182576
 0.7489635 -.0175272
 0.7741101 -.0167663
 0.7994059 -.0158447
 0.8246307 -.0146734
 0.8498041 -.0132224
 0.8749166 -.0115317
 0.8999583 -.0096812
 0.9249898 -.0077609
 0.9500108 -.0057805
 0.9750412 -.0036000
 1.0000000 -.0006400
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Polars for NASA/LANGLEY RC-08(N)1 AIRFOIL (rc08n1-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rc08n1-il50,000933.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rc08n1-il50,000533.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rc08n1-il100,000948.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rc08n1-il100,000545.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   rc08n1-il200,000963.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   rc08n1-il200,000556.7 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rc08n1-il500,000981.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rc08n1-il500,000567.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rc08n1-il1,000,000991.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rc08n1-il1,000,000576.8 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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