Goland Wing Examples

The function gen_goland_wing.m is installed with the BAFF toolbox, and can be used to generate a baff model of the Goland wing.

The Goland Wing is a classic test case for aeroelastic analysis. It is a simple cantilevered wing with a rectangular planform and a NACA 0012 airfoil. The wing is clamped at the root and free to deform in the vertical direction.

The primary properties of the Goland wing are:

Property	Value	Note
Span [m]	6.096	20ft span
Chord [m]	1.8288	6ft chord
EI [Nm^2]	9.77e6	bending rigidity
GJ [Nm^2]	0.99e6	torsional rigidity
mu [kg/m]	35.71	linear density
x_m [%]	43%	location of center of Mass (% of chord from LE)
x_f [%]	33%	location of elastic axis (% of chord from LE)
I_x [kg.m]	8.64	moment of inertia about elastic axis

Most of these values can be easily changed in the gen_goland_wing.m function; however, the Goland wing is generated by calling the function with no arguments.

Some example analyses are found at the links below:

https://flow.byu.edu/Aeroelasticity.jl/dev/examples/goland-stability/

https://arc.aiaa.org/doi/pdf/10.2514/6.2011-1917

Anaylsis using the tools in the dcrg repository are to follow.