HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
HSNLF(1)-0213 AIRFOIL - NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil
| Details | Dat file | Parser | |
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(hsnlf213-il) HSNLF(1)-0213 AIRFOIL NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord. Max camber 1.4% at 32.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HSNLF(1)-0213 AIRFOIL
60. 60.
0.0000000 0.0000000
0.0002081 0.0030156
0.0004404 0.0042896
0.0006768 0.0052722
0.0009152 0.0061014
0.0013960 0.0074893
0.0018798 0.0086523
0.0023657 0.0096695
0.0048113 0.0135796
0.0097387 0.0188041
0.0196455 0.0255093
0.0295765 0.0304662
0.0395197 0.0345513
0.0494700 0.0381238
0.0594256 0.0413146
0.0793488 0.0468303
0.0893149 0.0492664
0.0992833 0.0515290
0.1242134 0.0565480
0.1491534 0.0608503
0.1741017 0.0645565
0.1990572 0.0677428
0.2240189 0.0704807
0.2489862 0.0728205
0.2739588 0.0747781
0.2989362 0.0763869
0.3239183 0.0776567
0.3489050 0.0785958
0.3738961 0.0792244
0.3988915 0.0795402
0.4238911 0.0795538
0.4488952 0.0792429
0.4739037 0.0786115
0.4989173 0.0776188
0.5239361 0.0762416
0.5489615 0.0744017
0.5739940 0.0720512
0.5990348 0.0690951
0.6240846 0.0654873
0.6491438 0.0612047
0.6742112 0.0563390
0.6792255 0.0553066
0.6992846 0.0510353
0.7243610 0.0455240
0.7494381 0.0399538
0.7745122 0.0345993
0.7795268 0.0335463
0.7995843 0.0293932
0.8196388 0.0254604
0.8246519 0.0245092
0.8497156 0.0199073
0.8747744 0.0156566
0.8998261 0.0119208
0.9198638 0.0091876
0.9248728 0.0085371
0.9499137 0.0055808
0.9749509 0.0028859
0.9799575 0.0024050
0.9899698 0.0015154
1.0000000 0.0006699
0.0000000 0.0000000
0.0002722 -.0015952
0.0005319 -.0022948
0.0007896 -.0028494
0.0010462 -.0033303
0.0015579 -.0041686
0.0020680 -.0048937
0.0025768 -.0055288
0.0051095 -.0078869
0.0101535 -.0110600
0.0202114 -.0152308
0.0302550 -.0183788
0.0402912 -.0209903
0.0503219 -.0232064
0.0603492 -.0251820
0.0803972 -.0286494
0.0904188 -.0302069
0.1004391 -.0316799
0.1254849 -.0349892
0.1505247 -.0378769
0.1755594 -.0403926
0.2005894 -.0425688
0.2256161 -.0445036
0.2506398 -.0462310
0.2756608 -.0477530
0.3006791 -.0490918
0.3256950 -.0502523
0.3507084 -.0512314
0.3757190 -.0520125
0.4007270 -.0526050
0.4257324 -.0530064
0.4507349 -.0532088
0.4757345 -.0531965
0.5007319 -.0530259
0.5257273 -.0527197
0.5507193 -.0521530
0.5757076 -.0513265
0.6006921 -.0502214
0.6256720 -.0487928
0.6506455 -.0469020
0.6756113 -.0444586
0.6806035 -.0438963
0.7005657 -.0411985
0.7254971 -.0362719
0.7504186 -.0306382
0.7753537 -.0259808
0.7803422 -.0251533
0.8002983 -.0220149
0.8202578 -.0191028
0.8252481 -.0184089
0.8502025 -.0151410
0.8751609 -.0121685
0.9001219 -.0093751
0.9200921 -.0072401
0.9250848 -.0067255
0.9500512 -.0043230
0.9750227 -.0022855
0.9800178 -.0019329
0.9900086 -.0012757
1.0000000 -.0006699
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Polars for HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hsnlf213-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 50,000 | 5 | 27.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 9 | 46 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 5 | 37.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 9 | 53.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 5 | 49.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 9 | 70.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 5 | 59.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 9 | 78.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 5 | 67.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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