NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
NASA/LANGLEY NLF 0414F AIRFOIL - NASA/Langley/Viken NLF(1)-0414F natural laminar flow airfoil
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(nlf414f-il) NASA/LANGLEY NLF 0414F AIRFOIL NASA/Langley/Viken NLF(1)-0414F natural laminar flow airfoil Max thickness 14.2% at 46.6% chord. Max camber 2.4% at 53.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY NLF 0414F AIRFOIL
43.0 40.0
0.0000000 0.0000000
0.0002094 0.0032797
0.0024032 0.0106837
0.0075199 0.0177575
0.0156058 0.0242425
0.0265241 0.0304597
0.0400431 0.0365741
0.0560369 0.0426230
0.0744421 0.0485159
0.0951302 0.0541870
0.1179169 0.0596196
0.1426732 0.0648149
0.1692863 0.0698309
0.1975920 0.0745702
0.2274915 0.0789500
0.2587907 0.0829001
0.2913420 0.0863393
0.3249547 0.0892465
0.3594246 0.0916002
0.3945049 0.0933135
0.4300910 0.0943827
0.4658635 0.0947739
0.5015802 0.0944966
0.5370910 0.0934517
0.5722421 0.0916209
0.6067503 0.0889526
0.6402998 0.0853921
0.6727199 0.0808877
0.7038118 0.0751160
0.7335511 0.0675314
0.7633430 0.0580612
0.7937308 0.0478613
0.8241454 0.0379971
0.8539022 0.0291099
0.8821820 0.0216244
0.9082243 0.0155438
0.9316924 0.0107129
0.9520135 0.0070130
0.9689228 0.0042629
0.9823112 0.0023427
0.9919964 0.0010932
0.9979467 0.0003898
1.0000000 0.0001959
0.0000000 0.0000000
0.0002217 -.0021140
0.0022841 -.0069216
0.0074238 -.0107903
0.0159347 -.0144468
0.0278726 -.0180257
0.0429800 -.0214800
0.0609524 -.0248220
0.0816471 -.0280287
0.1049076 -.0310793
0.1305626 -.0339305
0.1584566 -.0365595
0.1883933 -.0389607
0.2201672 -.0411107
0.2535623 -.0429745
0.2883051 -.0445354
0.3241533 -.0457801
0.3608882 -.0466806
0.3983647 -.0471698
0.4363414 -.0472223
0.4745037 -.0468228
0.5126616 -.0460074
0.5505865 -.0447514
0.5879576 -.0429205
0.6245060 -.0404731
0.6599402 -.0372181
0.6941310 -.0328830
0.7271526 -.0262009
0.7621386 -.0180301
0.7975130 -.0117427
0.8315642 -.0070185
0.8635970 -.0036384
0.8928488 -.0015343
0.9190598 -.0004323
0.9417190 0.0000367
0.9606961 0.0001832
0.9759963 0.0001791
0.9876149 0.0001215
0.9955088 -.0000158
1.0000110 -.0001959
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Polars for NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf414f-il | 50,000 | 9 | 24.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 50,000 | 5 | 23.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 100,000 | 9 | 35.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 100,000 | 5 | 34.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 200,000 | 9 | 55.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 200,000 | 5 | 53.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 500,000 | 9 | 80.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 500,000 | 5 | 77.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 1,000,000 | 9 | 104.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 1,000,000 | 5 | 95.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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