BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il)
BOEING VERTOL V(1.95)3009-1.25 AIRFOIL - Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil
| Details | Dat file | Parser | |
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(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord. Max camber 1.3% at 20.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING VERTOL V(1.95)3009-1.25 AIRFOIL
20. 20.
0.0000000 0.0000000
0.0052062 0.0116900
0.0128420 0.0193966
0.0254831 0.0274050
0.0506615 0.0375227
0.0757772 0.0440809
0.1008605 0.0488094
0.1509463 0.0536771
0.2009960 0.0564952
0.2510130 0.0574635
0.3010098 0.0572820
0.3509895 0.0561307
0.4009583 0.0543594
0.5008578 0.0486574
0.6007263 0.0411955
0.7005668 0.0321439
0.8003905 0.0221525
0.9002098 0.0119011
0.9501143 0.0064805
1.0000000 0.0005500
0.0000000 0.0000000
0.0048215 -.0101266
0.0122410 -.0146981
0.0246672 -.0188878
0.0495940 -.0230379
0.0745562 -.0251783
0.0995272 -.0268288
0.1494896 -.0289600
0.1994627 -.0304912
0.2494391 -.0318225
0.2994237 -.0327039
0.3494146 -.0332153
0.3994148 -.0332068
0.4994531 -.0310301
0.5995226 -.0270937
0.6996199 -.0215676
0.7997339 -.0151016
0.8998524 -.0083757
0.9499168 -.0047178
1.0000000 -.0005500
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Polars for BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v13009-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 5 | 28.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 9 | 36.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 5 | 39.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 9 | 49.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 5 | 53.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 9 | 72.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 5 | 71.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 9 | 88.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 5 | 86.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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