NLR-1T AIRFOIL (nlr1t-il)
NLR-1T AIRFOIL - Bell/NASA/NLR NLR-1T rotorcraft airfoil
| Details | Dat file | Parser | |
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(nlr1t-il) NLR-1T AIRFOIL Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord. Max camber 1.3% at 22.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NLR-1T AIRFOIL
33. 33.
0.0 0.0
0.00259 0.00704
0.00974 0.01524
0.02185 0.02296
0.03796 0.02972
0.05675 0.03588
0.07753 0.04098
0.09845 0.04469
0.12341 0.04741
0.15412 0.04986
0.18767 0.05188
0.22313 0.05345
0.26054 0.05459
0.29979 0.05531
0.34064 0.05565
0.38269 0.05560
0.42528 0.05518
0.46849 0.05438
0.51162 0.05323
0.55383 0.05175
0.59596 0.04992
0.63728 0.04774
0.67732 0.04524
0.71079 0.04291
0.73905 0.04017
0.76946 0.03644
0.80263 0.03140
0.84055 0.02533
0.87846 0.01901
0.90845 0.01421
0.93589 0.01020
0.96199 0.00651
1.00000 0.00104
0.0 0.0
0.00259 -0.00512
0.00974 -0.00867
0.02185 -0.01180
0.03796 -0.01465
0.05675 -0.01713
0.07753 -0.01929
0.09845 -0.02112
0.12341 -0.02299
0.15412 -0.02494
0.18767 -0.02671
0.22313 -0.02821
0.26054 -0.02944
0.29979 -0.03040
0.34064 -0.03104
0.38269 -0.03142
0.42528 -0.03150
0.46849 -0.03132
0.51162 -0.03080
0.55383 -0.02992
0.59596 -0.02867
0.63728 -0.02734
0.67732 -0.02580
0.71079 -0.02432
0.73905 -0.02305
0.76946 -0.02164
0.80263 -0.01996
0.84055 -0.01794
0.87846 -0.01571
0.90845 -0.01364
0.93589 -0.01087
0.96199 -0.00711
1.00000 -0.00104
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Polars for NLR-1T AIRFOIL (nlr1t-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlr1t-il | 50,000 | 9 | 29.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 50,000 | 5 | 28.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 9 | 38.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 5 | 39.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 9 | 53.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 5 | 52 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 9 | 70.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 5 | 80.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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