BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il)
BOEING VERTOL V43015-2.48 AIRFOIL - Boeing-Vertol V43015-2.48 rotorcraft airfoil
| Details | Dat file | Parser | |
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(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% 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 V43015-2.48 AIRFOIL
21. 21.
0.0000000 0.0000000
0.0100000 0.0412000
0.0200000 0.0522000
0.0300000 0.0608000
0.0400000 0.0680000
0.0500000 0.0741000
0.0750000 0.0861000
0.1000000 0.0941000
0.1250000 0.0998000
0.1500000 0.1036000
0.2000000 0.1071000
0.2500000 0.1078000
0.3000000 0.1062000
0.4000000 0.0991000
0.5000000 0.0885000
0.6000000 0.0750000
0.7000000 0.0593000
0.8000000 0.0416000
0.9000000 0.0217000
0.9500000 0.0109000
1.0000000 0.0000000
0.0000000 0.0000000
0.0100000 -.0096000
0.0200000 -.0130000
0.0300000 -.0150000
0.0400000 -.0166000
0.0500000 -.0179000
0.0750000 -.0202000
0.1000000 -.0230000
0.1250000 -.0265000
0.1500000 -.0300000
0.2000000 -.0365000
0.2500000 -.0412000
0.3000000 -.0441000
0.4000000 -.0460000
0.5000000 -.0440000
0.6000000 -.0392000
0.7000000 -.0320000
0.8000000 -.0233000
0.9000000 -.0130000
0.9500000 -.0068000
1.0000000 0.0000000
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Polars for BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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