BOEING VERTOL V13006-.7 AIRFOIL (v13006-il)
BOEING VERTOL V13006-.7 AIRFOIL - Boeing-Vertol V13006-.7 rotorcraft airfoil
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(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord. Max camber 0.9% at 20.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING VERTOL V13006-.7 AIRFOIL
21. 21.
0.0000001 0.0
0.0020625 0.0055647
0.0045858 0.0079296
0.0096073 0.0105647
0.0146265 0.0129998
0.0271536 0.0173410
0.0521836 0.0240278
0.0771898 0.0287186
0.1021828 0.0323116
0.1521293 0.0361047
0.2020521 0.0380019
0.2519568 0.0384023
0.3018544 0.0382037
0.4016305 0.0361106
0.5013863 0.0324207
0.6011277 0.0275328
0.7008607 0.0218470
0.8005842 0.0154633
0.9003004 0.0083806
0.9501550 0.0045893
1.0000000 0.0006000
0.0000001 0.0
0.0019346 -.0051135
0.0044066 -.0070393
0.0093743 -.0088949
0.0143505 -.0100526
0.0268045 -.0117988
0.0517271 -.0140935
0.0766580 -.0156902
0.1015960 -.0166869
0.1514768 -.0183824
0.2013600 -.0197779
0.2512469 -.0208744
0.3011386 -.0215720
0.4009373 -.0217692
0.5007529 -.0204695
0.6005828 -.0179719
0.7004234 -.0146763
0.8002711 -.0106828
0.9001283 -.0059903
0.9500594 -.0033941
1.0000000 -.0006000
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Polars for BOEING VERTOL V13006-.7 AIRFOIL (v13006-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v13006-il | 50,000 | 9 | 27.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 50,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 9 | 37.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 5 | 35.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 9 | 46.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 5 | 41.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 9 | 54.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 9 | 62.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 5 | 64.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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