Lift & Drag
Flight conditions
Wing geometry
Airfoil
Aerodynamic forces and coefficients
The existing force balance and coefficient curve show the selected operating point and stall boundary.
Force balance
Lift vector
17,139 N
Drag vector
1,370 N
Angle (α)
5.0°
Free-stream
reference line
Coefficient curve
Lift force
17,139.33 N
CL 0.771
Drag force
1,370.37 N
CD 0.0616
Lift/drag ratio
12.5
Maximum 21.1
Stall speed
8.96 m/s
32.26 km/h
Optimal angle of attack
0.3 deg
For maximum lift/drag ratio
Aspect ratio
4.0
Span squared divided by area
Velocity
50.00 m/s
180.00 km/h, 97.19 knots
Altitude
1,000.00 m
3,280.84 ft
Air density
1.1117 kg/m3
Dynamic pressure 1,389.56 Pa
Airfoil
NACA 2412
CL max 1.40, CD0 0.0060
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