BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il)
BELL/WORTMANN FX 69-H-083 AIRFOIL - Bell/Wortmann FX 69-H-083 rotorcraft airfoil
| Details | Dat file | Parser | |
|
(fx69h083-il) BELL/WORTMANN FX 69-H-083 AIRFOIL Bell/Wortmann FX 69-H-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord. Max camber 2.5% at 33.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BELL/WORTMANN FX 69-H-083 AIRFOIL
27. 27.
0.0 0.0
0.00550 0.00820
0.01110 0.01230
0.01670 0.01570
0.02220 0.01870
0.02780 0.02130
0.03890 0.02590
0.05560 0.03180
0.08330 0.03910
0.11110 0.04590
0.13890 0.05050
0.16670 0.05530
0.22220 0.06150
0.27780 0.06510
0.33330 0.06640
0.38890 0.06610
0.44440 0.06430
0.50000 0.06120
0.55550 0.05680
0.61110 0.05150
0.66670 0.04520
0.72220 0.03800
0.77770 0.03010
0.83330 0.02180
0.88880 0.01340
0.94440 0.00590
1.00000 0.00050
0.0 0.0
0.00550 -.00500
0.01110 -.00680
0.01670 -.00800
0.02220 -.00900
0.02780 -.00980
0.03890 -.01110
0.05560 -.01240
0.08330 -.01390
0.11110 -.01490
0.13890 -.01560
0.16670 -.01610
0.22220 -.01680
0.27780 -.01720
0.33330 -.01760
0.38890 -.01780
0.44440 -.01810
0.50000 -.01800
0.55550 -.01760
0.61110 -.01690
0.66670 -.01610
0.72220 -.01510
0.77770 -.01380
0.83330 -.01190
0.88880 -.00910
0.94440 -.00550
1.00000 -.00140
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx69h083-il | 50,000 | 9 | 36.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 9 | 53 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 9 | 69.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 5 | 66.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 9 | 90.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 5 | 78.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 9 | 101 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 5 | 81.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||