BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il)
BOEING-VERTOL V23010-1.58 AIRFOIL - Boeing-Vertol V23010-1.58 rotorcraft airfoil
| Details | Dat file | Parser | |
|
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord. Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL V23010-1.58 AIRFOIL
26. 26.
0.0 0.0
0.0099884 0.0192060
0.0199836 0.0270120
0.0299799 0.0331180
0.0499741 0.0428300
0.0749690 0.0514449
0.0999656 0.0570598
0.1249631 0.0612748
0.1499614 0.0641899
0.1999602 0.0662197
0.2499603 0.0659497
0.2999610 0.0649799
0.3499621 0.0630098
0.3999636 0.0605399
0.4499654 0.0574699
0.4999677 0.0536999
0.5499704 0.0493299
0.5999732 0.0446599
0.6499763 0.0394899
0.6999798 0.0337199
0.7499831 0.0281499
0.7999862 0.0229800
0.8499898 0.0170100
0.8999931 0.0115400
0.9499966 0.0056700
1.0000000 0.0
0.0 0.0
0.0100089 -.0150940
0.0200104 -.0175880
0.0300112 -.0189820
0.0500122 -.0205700
0.0750135 -.0226550
0.1000147 -.0247400
0.1250160 -.0268250
0.1500173 -.0291100
0.2000195 -.0326800
0.2500211 -.0353500
0.3000220 -.0368200
0.3500222 -.0370900
0.4000220 -.0367600
0.4500213 -.0355299
0.5000202 -.0337999
0.5500188 -.0314699
0.6000172 -.0287399
0.6500152 -.0254100
0.7000133 -.0221800
0.7500111 -.0185500
0.8000090 -.0149200
0.8500068 -.0111900
0.9000045 -.0075600
0.9500023 -.0038300
1.0000000 0.0
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v23010-il | 50,000 | 9 | 23.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 50,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 9 | 35.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 5 | 41.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 9 | 54.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 5 | 57.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 9 | 79.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 5 | 78 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 9 | 97.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 5 | 94.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||