SIKORSKY DBLN-526 AIRFOIL (dbln526-il)
SIKORSKY DBLN-526 AIRFOIL - Sikorsky DBLN-526 double ended rotorcraft airfoil
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(dbln526-il) SIKORSKY DBLN-526 AIRFOIL Sikorsky DBLN-526 double ended rotorcraft airfoil Max thickness 26% at 50% chord. Max camber 4% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
SIKORSKY DBLN-526 AIRFOIL 23. 23. 0.0000 0.0000 0.0125 0.0362 0.0250 0.0491 0.0500 0.0679 0.0750 0.0823 0.1000 0.0952 0.1500 0.1152 0.2000 0.1302 0.2500 0.1430 0.3000 0.1530 0.4000 0.1668 0.5000 0.1698 0.6000 0.1668 0.7000 0.1530 0.7500 0.1430 0.8000 0.1302 0.8500 0.1152 0.9000 0.0952 0.9250 0.0823 0.9500 0.0679 0.9750 0.0491 0.9875 0.0362 1.0000 0.0000 0.0000 0.0000 0.0125 -.0208 0.0250 -.0298 0.0500 -.0405 0.0750 -.0483 0.1000 -.0548 0.1500 -.0637 0.2000 -.0708 0.2500 -.0751 0.3000 -.0823 0.4000 -.0887 0.5000 -.0901 0.6000 -.0887 0.7000 -.0823 0.7500 -.0751 0.8000 -.0708 0.8500 -.0637 0.9000 -.0548 0.9250 -.0483 0.9500 -.0405 0.9750 -.0298 0.9875 -.0208 1.0000 0.0000 |
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Polars for SIKORSKY DBLN-526 AIRFOIL (dbln526-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dbln526-il | 50,000 | 9 | 4.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 50,000 | 5 | 10.8 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 100,000 | 9 | 20 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 100,000 | 5 | 19.7 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 200,000 | 9 | 35 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 200,000 | 5 | 31 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 500,000 | 9 | 47.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 500,000 | 5 | 41.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 1,000,000 | 9 | 53.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 1,000,000 | 5 | 34.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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