NLR-7223-62 AIRFOIL (nl722362-il)
NLR-7223-62 AIRFOIL - NLR NLR-7223-62 transonic rotorcraft airfoil
| Details | Dat file | Parser | |
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(nl722362-il) NLR-7223-62 AIRFOIL NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord. Max camber 1.3% at 21.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NLR-7223-62 AIRFOIL
74. 59.
0.0 0.0
0.00125 0.00617
0.00416 0.01023
0.00978 0.01508
0.01748 0.02005
0.02729 0.02515
0.03956 0.03017
0.04498 0.03207
0.05219 0.03435
0.05969 0.03648
0.06728 0.03842
0.07672 0.04057
0.08617 0.04243
0.08977 0.04307
0.09217 0.04346
0.09337 0.04365
0.09457 0.04384
0.09577 0.04401
0.09766 0.04428
0.09955 0.04453
0.10145 0.04476
0.10522 0.04521
0.10901 0.04563
0.11493 0.04624
0.11871 0.04662
0.12628 0.04730
0.13619 0.04815
0.14943 0.04915
0.16266 0.05004
0.17401 0.05074
0.18724 0.05146
0.20093 0.05212
0.21605 0.05275
0.22738 0.05317
0.24162 0.05363
0.25673 0.05404
0.27184 0.05438
0.28701 0.05465
0.30211 0.05486
0.31722 0.05501
0.33421 0.05512
0.34814 0.05516
0.36513 0.05514
0.38024 0.05508
0.39533 0.05497
0.41232 0.05478
0.42929 0.05455
0.44628 0.05425
0.46137 0.05394
0.47976 0.05351
0.49485 0.05310
0.51353 0.05254
0.53239 0.05189
0.54748 0.05133
0.56635 0.05055
0.58091 0.04991
0.59600 0.04919
0.61263 0.04833
0.62960 0.04740
0.64741 0.04635
0.66250 0.04539
0.67758 0.04438
0.71085 0.04192
0.73974 0.03909
0.76970 0.03505
0.79864 0.03053
0.82615 0.02614
0.85176 0.02196
0.87705 0.01772
0.90954 0.01262
0.94056 0.00820
0.97405 0.00345
0.98674 0.00161
1.00000 0.00000
0.0 0.0
0.00054 -.00251
0.00118 -.00363
0.00265 -.00520
0.00450 -.00641
0.00730 -.00765
0.00992 -.00860
0.01334 -.00964
0.01749 -.01072
0.02181 -.01170
0.02769 -.01286
0.03500 -.01411
0.03938 -.01477
0.04638 -.01573
0.05274 -.01654
0.06154 -.01754
0.06978 -.01840
0.07732 -.01913
0.08778 -.02008
0.09531 -.02072
0.10662 -.02162
0.11645 -.02234
0.12776 -.02313
0.13908 -.02387
0.15039 -.02455
0.16170 -.02520
0.17490 -.02589
0.18864 -.02656
0.20185 -.02714
0.21505 -.02768
0.22825 -.02817
0.24145 -.02862
0.25655 -.02908
0.27168 -.02949
0.28678 -.02985
0.31696 -.03043
0.34904 -.03083
0.38098 -.03107
0.41307 -.03115
0.44726 -.03106
0.48125 -.03078
0.51389 -.03030
0.54720 -.02959
0.58067 -.02861
0.61492 -.02754
0.64771 -.02638
0.67813 -.02512
0.70940 -.02375
0.74105 -.02238
0.76943 -.02097
0.79937 -.01947
0.82514 -.01805
0.85298 -.01653
0.87654 -.01505
0.90896 -.01250
0.94070 -.00885
0.97353 -.00352
0.98677 -.00135
1.00000 0.00000
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Polars for NLR-7223-62 AIRFOIL (nl722362-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nl722362-il | 50,000 | 9 | 30 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 50,000 | 5 | 28.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 9 | 42.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 9 | 57.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 9 | 72.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 5 | 70.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 9 | 87.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 5 | 78.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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