BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il)
BOEING VERTOL V43012-1.58 AIRFOIL - Boeing-Vertol V43012-1.58 rotorcraft airfoil
| Details | Dat file | Parser | |
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(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord. Max camber 3.7% at 15% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING VERTOL V43012-1.58 AIRFOIL
37. 37.
0.0000000 0.0000000
0.0100000 0.0321000
0.0200000 0.0423000
0.0300000 0.0503000
0.0400000 0.0571000
0.0500000 0.0631000
0.0750000 0.0745000
0.0900000 0.0791000
0.1100000 0.0840000
0.1250000 0.0869000
0.1500000 0.0901000
0.1800000 0.0920000
0.2100000 0.0929000
0.2450000 0.0926000
0.2800000 0.0920000
0.3200000 0.0905000
0.3600000 0.0880000
0.4000000 0.0850000
0.4400000 0.0820000
0.4800000 0.0780000
0.5200000 0.0733000
0.5600000 0.0685000
0.6000000 0.0635000
0.6400000 0.0582000
0.6800000 0.0527000
0.7200000 0.0469000
0.7600000 0.0410000
0.8000000 0.0350000
0.8300000 0.0301000
0.8600000 0.0253000
0.8900000 0.0203000
0.9100000 0.0167000
0.9250000 0.0140000
0.9400000 0.0113000
0.9550000 0.0084000
0.9800000 0.0038000
1.0000000 0.0000000
0.0000000 0.0000000
0.0100000 -.0077000
0.0200000 -.0090000
0.0300000 -.0100000
0.0400000 -.0108000
0.0500000 -.0108000
0.0750000 -.0110000
0.0900000 -.0115000
0.1100000 -.0130000
0.1250000 -.0142000
0.1500000 -.0167000
0.1800000 -.0200000
0.2100000 -.0231000
0.2450000 -.0260000
0.2800000 -.0281000
0.3200000 -.0299000
0.3600000 -.0310000
0.4000000 -.0315000
0.4400000 -.0314000
0.4800000 -.0310000
0.5200000 -.0304000
0.5600000 -.0293000
0.6000000 -.0279000
0.6400000 -.0263000
0.6800000 -.0244000
0.7200000 -.0222000
0.7600000 -.0198000
0.8000000 -.0172000
0.8300000 -.0149000
0.8600000 -.0125000
0.8900000 -.0100000
0.9100000 -.0084000
0.9250000 -.0070000
0.9400000 -.0057000
0.9550000 -.0043000
0.9800000 -.0020000
1.0000000 0.0000000
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Polars for BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43012-il | 50,000 | 9 | 24 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 50,000 | 5 | 28.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 9 | 36.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 5 | 40.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 9 | 50.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 5 | 55.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 9 | 77.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 5 | 81.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 5 | 101.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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