Aerospace Structural Analysis :MATLAB Programming Projects
- Subject Code :
SE-260A
1.) Calculate the section properties for the following T-section with (b = 2.0”, h = 1.0”, and t = 0.1”)
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2.) Calculate the inertia properties for the T-section of problem (#1) with (xo=yo=0) at orientation
angles of (alpha = 0, 45, 90, 135, 180, and 270). Put your answers in this table.
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3.) Calculate the section properties in the (x”, y”) frame for the following z-section at (alpha = 0 and 90) with ( x and y degree =0)
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4.) Calculate the section properties for the following rectangle with a triangular hole.
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5.) Calculate the section properties for three different propeller airfoil thicknesses; a thin tip (NACA-0008), a mid-length (NACA-0012), and thick root (NACA-0016). Also calculate the section properties for a highly cambered airfoil (NACA-4412). Assume all four chord lengths are (co =10”). Fill out the table for the following section properties that are normalized to the chord (co)and maximum thickness (tmax). Comment on the ability of (co) and (tmax) to normalize the section properties for the symmetric airfoil sections.
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