Question 4 of 8: Principal Stresses and Maximum Shear Stress by Mohr's Circle
Nivaar worked solution (AI-drafted; not reviewed by a licensed engineer)
Notes on this paper
National Exam, May 2019 — 04-BS-06: Mechanics of Materials. Closed book, one 8.5"×11" handwritten aid sheet permitted, 3 hours, 8 questions of equal value (any 5 of 8 constitute a complete paper — all 8 are answered here as a complete study resource).
Reference texts: R.C. Hibbeler, Mechanics of Materials, 10th ed. (Pearson) — axial deformation of statically indeterminate assemblies, beam deflection by integration, shear/moment diagrams, plane-stress transformation and Mohr's circle, column buckling, torsion of circular shafts, composite (transformed-section) beams, combined axial-flexural loading, transverse shear.
Question 4: Principal Stresses and Maximum Shear Stress by Mohr's Circle
Mohr's circle: center 90 MPa, R=84.85 MPa; sigma1/sigma2/tau_max marked.
Approach. Plot points $X=(\sigma_x,-\tau_{xy})$ and $Y=(\sigma_y,\tau_{xy})$, the diameter of Mohr's circle; the center and radius give $\sigma_{1,2}$ directly, and the angle to $X$ gives the physical rotation to the principal plane.
Circle center and radius.
$$\sigma_{avg}=\frac{\sigma_x+\sigma_y}{2}=\frac{150+30}{2}=90\text{ MPa}$$
$$R=\sqrt{\left(\frac{\sigma_x-\sigma_y}{2}\right)^2+\tau_{xy}^2}=\sqrt{60^2+60^2}=84.85\text{ MPa}$$
Part (a) — Principal stresses.
$$\boxed{\sigma_1=\sigma_{avg}+R=174.85\text{ MPa},\qquad \sigma_2=\sigma_{avg}-R=5.15\text{ MPa}}$$
Part (b) — Orientation of the principal plane. From the circle, the angle from point $X$ to the $\sigma_1$ axis is
$$2\theta_p=\tan^{-1}\!\left(\frac{\tau_{xy}}{(\sigma_x-\sigma_y)/2}\right)=\tan^{-1}(1)=45^{\circ}\Rightarrow \theta_p=22.5^{\circ}$$
Rotating the stress element $22.5^{\circ}$ counterclockwise from the $x$-face aligns it with the $\sigma_1=174.85$ MPa plane (the $\sigma_2$ plane is $90^{\circ}$ away, perpendicular).
Part (c)&(d) — Maximum shear stress and its plane. The top of the circle gives
$$\boxed{\tau_{max}=R=84.85\text{ MPa},\ \text{with an average normal stress }\sigma_{avg}=90\text{ MPa on that plane}}$$
located at $\theta_s=\theta_p-45^{\circ}=-22.5^{\circ}$ (i.e. $22.5^{\circ}$ clockwise from the $x$-face) — always $45^{\circ}$ from the principal planes.
Result
Value
$\sigma_1$
174.85 MPa, at $\theta_p=22.5^{\circ}$ CCW from x-axis
$\sigma_2$
5.15 MPa, at $\theta_p+90^{\circ}$
$\tau_{max}$
84.85 MPa, at $\theta_s=-22.5^{\circ}$ ($\sigma_{avg}=90$ MPa on that face)