NASA/LANGLEY RC-08(N)1 AIRFOIL (rc08n1-il)
NASA/LANGLEY RC-08(N)1 AIRFOIL - NASA/Langley RC-08(N)1 rotorcraft airfoil
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc08n1-il | 50,000 | 9 | 33.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 50,000 | 5 | 33.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 9 | 48.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 5 | 45.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 9 | 63.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 5 | 56.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 9 | 81.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 5 | 67.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 9 | 91.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 5 | 76.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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