Question 1

Material Testing — Tensile Test on Mild Steel After fracture in a standard tensile test on a round bar of mild steel, how does the local diameter at the fracture section change?

Accepted Answer

Introduction: A tensile test reveals elastic properties, yielding, strain hardening, necking, and ductile fracture of metals such as mild steel. The visible change in cross-section at the fracture provides direct evidence of ductility. Given Data / Assumptions: Specimen: round bar of mild steel (ductile material). Standard uniaxial tensile test to fracture. Uniform temperature, quasi-static loading. Concept / Approach: After uniform elongation, a ductile metal enters diffuse necking, then localized necking. True stress rises even as engineering stress may drop. Cross-section reduces markedly at the neck just before ductile fracture (cup-and-cone profile). Step-by-Step Solution: Elastic region: diameter change negligible and recoverable.Plastic region: volume constancy approximately holds, so as length increases, area must reduce.Necking: localized reduction in area causes a sharp decrease in diameter at the neck.Fracture: the broken ends show smaller diameter where necking developed. Verification / Alternative check: Fracture surface and gauge length measurements show reduction of area = ((A0 - Af) / A0) * 100%. Why Other Options Are Wrong: remain same: contradicts measured reduction of area in ductile fracture.increase: impossible under tensile necking.depend upon rate of loading: normal quasi-static tests still show necking; rate effects do not reverse the trend. Common Pitfalls: Confusing engineering stress–strain with true stress–strain and misinterpreting the post-UTS behavior. Final Answer: decrease

Question 2

Columns — Effective (Equivalent) Length For a column with one end fixed and the other end hinged (pin), what is the correct relation between equivalent length L and actual length l?

Accepted Answer

Introduction: Euler buckling strength depends on the effective (equivalent) length, which incorporates end restraints. Different end conditions lead to different buckling half-wavelengths, captured by L = K * l, where K is an end-condition factor. Given Data / Assumptions: Straight prismatic column, elastic behavior. One end fixed (no rotation, no translation), other end hinged (rotation free, no translation). Axial concentric compression. Concept / Approach: For fixed–pinned columns, the end-condition factor K is approximately 0.7. In many exam standards, this is exactly taken as 1/√2 ≈ 0.707. Thus, the equivalent length L = K * l = l/√2. Step-by-Step Solution: General Euler: P_cr = (pi^2 * E * I) / (L^2)Introduce L = K * l for end restraints.For fixed–pinned: K ≈ 0.7; widely tabulated as K = 1/√2.Therefore L = l/√2 gives the correct effective length. Verification / Alternative check: Compare to other cases: pinned–pinned K = 1, fixed–fixed K = 0.5, fixed–free K = 2. The value for fixed–pinned fits this sequence. Why Other Options Are Wrong: L = l/2: corresponds to fixed–fixed, not fixed–pinned.L = l: corresponds to pinned–pinned.L = 2l: corresponds to fixed–free (cantilever). Common Pitfalls: Memorizing formulas without linking them to end restraints and mode shapes. Final Answer: L = l/√2

Question 3

Torsion of Hollow Shafts — Polar Modulus What is the polar section modulus (Z_p) for a hollow circular shaft with outer diameter D and inner diameter d?

Accepted Answer

Introduction: Polar section modulus relates torsional moment to maximum shear stress. For shafts, it is defined as Z_p = J / R, where J is polar moment of inertia and R is outer radius. Given Data / Assumptions: Hollow circular shaft with outer diameter D and inner diameter d. Elastic torsion, circular shafts, Saint-Venant theory. Maximum shear occurs at outer surface (radius R = D/2). Concept / Approach: For a hollow circular section, J = (pi/32) * (D^4 - d^4). The polar section modulus is Z_p = J / R = J / (D/2) = (2J) / D. Step-by-Step Solution: Compute J: J = (pi/32) * (D^4 - d^4)Set R = D/2Z_p = J / R = ((pi/32) * (D^4 - d^4)) / (D/2)Simplify: Z_p = (pi/16) * (D^4 - d^4) / D Verification / Alternative check: Dimension check: numerator has length^4; dividing by D gives length^3, consistent with section modulus. Why Other Options Are Wrong: Option a: same as correct but unsimplified; both evaluate numerically equal, yet standard compact form is option b.Option c: uses D^4 + d^4, which is incorrect for hollow sections.Option d: mixes constants incorrectly and leads to a wrong multiplier. Common Pitfalls: Confusing J (pi/32)*(D^4 - d^4) with I (pi/64)*D^4 for bending. Final Answer: Z_p = (pi/16) * (D^4 - d^4) / D

Question 4

Flexure Formula — Bending Equation Which relation correctly represents the bending equation linking bending moment, curvature, and stress distribution for pure bending of a prismatic beam?

Accepted Answer

Introduction: The classic flexure formula connects internal bending moment with the linear stress distribution and beam curvature under pure bending for linearly elastic materials. Given Data / Assumptions: Prismatic beam, homogeneous and isotropic. Pure bending region (no shear), small deflection theory. Plane sections remain plane, linear elastic behavior. Concept / Approach: The bending equation is derived from strain compatibility and Hooke's law. It states that normal stress varies linearly with distance y from the neutral axis, and curvature is proportional to bending moment through E and I. Step-by-Step Solution: Strain at a fiber: epsilon = y / RStress: sigma = E * epsilon = E * (y / R)Resultant moment: M = integral(sigma * y dA) = (E/R) * integral(y^2 dA) = (E/R) * IRearrange: M / I = sigma / y = E / R Verification / Alternative check: Units: M/I has units of stress/curvature; sigma/y equals E/R, consistent dimensionally. Why Other Options Are Wrong: M / y = sigma / I = R / E: inverts terms incorrectly.M / I = y / sigma = R / E: places y and sigma in the wrong ratio.M * I = sigma * y = E * R: incorrect dimensional relation. Common Pitfalls: Using y with sign mistakes and misidentifying the neutral axis where sigma = 0. Final Answer: M / I = sigma / y = E / R

Question 5

Riveted Joints — Patterns A joint in which the number of rivets decreases from the innermost row to the outermost row is called what type of riveted joint?

Accepted Answer

Introduction: Riveted joint efficiency and load flow depend on the arrangement of rivets. Different patterns balance shear and bearing while limiting tearing and cracking paths. Given Data / Assumptions: Multi-row riveted lap or butt joint. Rivet count reduces from center (innermost) toward the edges (outermost). Concept / Approach: When rivet numbers taper along rows so that the pattern forms a diamond shape, the joint is termed diamond riveted. This layout tries to distribute stresses more uniformly and shorten potential tear paths. Step-by-Step Solution: Identify the pattern: central row has the most rivets.Outer rows have progressively fewer rivets.Visual layout resembles a diamond; therefore, the joint is diamond riveted. Verification / Alternative check: Compare with chain (aligned columns) and zig-zag (staggered but constant count) to see the distinguishing reduction in count outward. Why Other Options Are Wrong: chain riveted: rows directly opposite each other with constant count.zig-zag riveted: staggered arrangement but no systematic reduction outward.none of these: incorrect because the described pattern matches the named diamond riveted joint. Common Pitfalls: Confusing stagger (zig-zag) with taper (diamond); these are separate characteristics. Final Answer: diamond riveted

Question 6

Impact vs Gradual Loading — Strain Energy For a linear elastic member, the strain energy stored when a load is applied suddenly (without initial velocity) is how many times the strain energy stored when the same load is applied gradually?

Accepted Answer

Introduction: Energy methods compare how loading history influences internal energy and maximum stresses. A classic result contrasts gradual (static) loading with a sudden application of the same load in linear elasticity. Given Data / Assumptions: Linearly elastic member (Hooke's law). Load P applied either gradually (from 0 to P) or suddenly (instantaneous but without impact velocity). No damping; mass effects only through equilibrium of the final state for the sudden case. Concept / Approach: Under gradual loading, maximum deflection is delta, and strain energy U_gradual = (1/2) * P * delta. For sudden loading, the system oscillates and the maximum static-equivalent deformation reaches 2 * delta, giving double the strain energy. Step-by-Step Solution: Gradual: U_g = (1/2) * P * deltaSudden: peak force equals P but deflection doubles: delta_max = 2 * deltaU_sudden = (1/2) * P * (2 * delta) = P * delta = 2 * U_g Verification / Alternative check: Equivalent spring model with stiffness k: delta = P / k; sudden case yields maximum extension 2 * (P / k). Why Other Options Are Wrong: equal to: ignores dynamic amplification.one-half: opposite of the correct amplification.four times: would require additional kinetic impact (drop), not a mere sudden application without velocity. Common Pitfalls: Confusing sudden loading (no drop height) with impact loading from a height, which can produce larger factors. Final Answer: twice

Question 7

Section Modulus — Solid Circular Section What is the section modulus Z about a centroidal axis for a solid circular section of diameter d?

Accepted Answer

Introduction: Section modulus links bending moment to extreme-fiber stress: sigma_max = M / Z. For a solid circle, Z depends on its centroidal second moment of area and the outermost fiber distance. Given Data / Assumptions: Solid circular cross-section of diameter d. Centroidal bending about any diametral axis. Concept / Approach: For a solid circle, I = (pi * d^4) / 64 about a centroidal axis. The extreme distance is y_max = d / 2. Hence Z = I / y_max. Step-by-Step Solution: I = (pi * d^4) / 64y_max = d / 2Z = I / y_max = ((pi * d^4) / 64) / (d / 2) = (pi * d^3) / 32 Verification / Alternative check: Dimensional check: length^4 divided by length gives length^3, correct for Z. Why Other Options Are Wrong: pi * d^2 / 4 and pi * d^2 / 16: these correspond to areas, not section modulus.pi * d^3 / 16: off by a factor of 2; incorrect denominator. Common Pitfalls: Mixing up I with J (polar) or area A with Z; always confirm the correct formula. Final Answer: pi * d^3 / 32

Question 8

Thin Cylindrical Pressure Vessels The hoop stress developed in a thin-walled cylindrical shell under internal pressure is best described as which type of stress?

Accepted Answer

Introduction: Thin-walled pressure vessels develop two main membrane stresses: circumferential (hoop) and longitudinal. Understanding their nature guides safe design of boilers, pipes, and tanks. Given Data / Assumptions: Thin cylinder: wall thickness t much smaller than diameter. Uniform internal pressure p. Neglect radial stress through thickness compared to membrane stresses. Concept / Approach: The hoop stress acts tangentially around the circumference and is tensile. In contrast, longitudinal stress acts along the axis, and radial stress across thickness is small for thin shells. Step-by-Step Solution: Hoop stress magnitude: sigma_h = p * d / (2 * t)Longitudinal stress magnitude: sigma_l = p * d / (4 * t)Direction: sigma_h is circumferential tension; sigma_l is axial tension; radial stress is compressive on the inner surface but negligible for thin shells. Verification / Alternative check: Free-body of half-cylinder shows hoop force balancing pressure on the cut; algebra yields sigma_h as above, confirming tensile circumferential action. Why Other Options Are Wrong: longitudinal stress: different direction; not the hoop stress.compressive stress: hoop is tensile for internal pressure.radial stress: small in thin shells and not the defined hoop stress. Common Pitfalls: Confusing magnitudes and directions; remember sigma_h = 2 * sigma_l for thin cylinders. Final Answer: circumferential tensile stress

Question 9

Torsion of circular shafts — choose the correct unified torsion equation below (valid for homogeneous, isotropic shafts under elastic twist). State the standard relationship among applied torque, polar moment of inertia, maximum shear stress at the …

Accepted Answer

Introduction: In strength of materials, the elastic torsion of circular shafts is governed by one compact relation that links torque, section geometry, shear stress, material stiffness in shear, and twist. Identifying the correct form tests understanding of symbols and the assumptions of linear elasticity. Given Data / Assumptions: Prismatic, circular shaft; homogeneous and isotropic. Small deformations; linear elastic behavior. Symbols: T (torque), J (polar moment of inertia), τ (shear stress at radius R), R (outer radius), G (shear modulus), θ (angle of twist in radians), L (gauge length). Concept / Approach: The torsion formula for circular shafts simultaneously expresses stress distribution and angular twist. J is for torsion (not I), and G controls shear deformation (not E). Step-by-Step Solution: Shear stress distribution: τ(r) = Tr/J, hence τ_max at r = R is τ = TR/JTwist-geometry relation: θ = (TL)/(JG)Combine to get the unified equation: T/J = τ/R = Gθ/L Verification / Alternative check: Dimensional check confirms consistency: [T]/[L^4] = [stress]/[length] = [modulus][rotation]/[length]. Why Other Options Are Wrong: Uses σ or E: bending/axial symbols (incorrect for torsion). Using I or y belongs to bending (T/I or σ/y are bending analogs). Replacing G with E confuses shear and normal stiffness. Common Pitfalls: Mixing I with J; swapping E and G; omitting the outer radius R when relating τ and T. Final Answer: T/J = τ/R = G*θ/L

Question 10

Elastic (bending) strength comparison of two rectangular beams with identical width b and depth d: Beam A has length l; Beam B has length 2l. For the same material and cross-section, how does the elastic strength in bending of Beam B compare with Be…

Accepted Answer

Introduction: "Elastic strength in bending" refers to the maximum bending stress capacity governed by material yield/allowable stress and section modulus, not by member length. This question checks whether you distinguish strength (stress capacity) from deflection (stiffness). Given Data / Assumptions: Both beams: same rectangular section (b by d) and same material. Only length differs: l vs 2l. Strength reference is section capacity in the elastic range. Concept / Approach: For bending, maximum normal stress σ_max = M_max / Z, where Z = bd^2/6 for a rectangle. Strength capacity depends on Z and material limit; it does not directly depend on span. Span affects M_max only for a specific loading pattern, but the intrinsic elastic strength (capacity per unit bending moment) is unchanged by length if b and d are fixed. Step-by-Step Solution: Section modulus (both beams): Z = bd^2/6 (identical)Allowable bending stress (both): σ_allow = M/Z ⇒ capacity tied to Z and materialSince Z and material are the same, elastic bending strength is the same Verification / Alternative check: If both are subjected to the same bending moment at a section, the computed stress σ = M/Z is identical because Z is identical. Why Other Options Are Wrong: one-half / one-fourth / one-eighth: These imply strength scaling with length, which is incorrect for intrinsic bending strength. greater than Beam A: No increase without a change in section or material. Common Pitfalls: Confusing strength with deflection or moment due to a particular load case; span affects deflection and internal M for a given load pattern, but not the intrinsic section strength. Final Answer: same

Question 11

Thin pressure vessel criterion — classify a shell as thin or thick: A pressure vessel is considered a thin shell when the wall-thickness-to-diameter ratio (t/D) is __________ 1/10.

Accepted Answer

Introduction: Design formulas for thin pressure vessels assume membrane action with negligible through-thickness stress gradient. The classification relies on the ratio t/D (thickness to diameter). Given Data / Assumptions: t is wall thickness; D is mean diameter. Empirical demarcations separate thin and thick shell theories. Concept / Approach: When t/D is small, hoop and longitudinal stresses vary little across the wall, so thin-shell formulas are valid. Many textbooks adopt thresholds such as t/D ≤ 1/10 (or more conservatively ≤ 1/20); the key idea is "less than" a small fraction of diameter. Step-by-Step Solution: Identify criterion asked: compare t/D with 1/10Thin shell if t/D is sufficiently small relative to diameterHence: t/D less than 1/10 Verification / Alternative check: For very small t/D, radial stress is negligible compared to hoop/longitudinal membrane stresses, validating thin-shell equations like σ_hoop = pD/(2t). Why Other Options Are Wrong: equal to / approximately equal to: boundary conditions are conservative; equality is not the intended general rule. greater than: would indicate a thick shell, invalidating thin formulas. not applicable: classification is central to pressure vessel analysis. Common Pitfalls: Confusing different conservative thresholds (1/10 vs 1/20). The safer interpretation is that t/D must be less than a small fraction of diameter for thin-shell theory to hold. Final Answer: less than

Question 12

Assessing shaft capacity — is the strength of a circular shaft judged by the maximum torque it can safely transmit?

Accepted Answer

Introduction: Shaft design involves two criteria: strength (stress) and rigidity (twist). This item asks whether strength assessment is fundamentally linked to the torque-carrying capacity. Given Data / Assumptions: Homogeneous, isotropic shaft; elastic behavior. Failure governed by allowable shear stress. Concept / Approach: Strength is about stress not exceeding an allowable limit. In torsion, τ_max = TR/J; thus, the largest safe torque determines whether the shaft is strong enough. Rigidity uses θ = TL/(JG) and is a separate serviceability check. Step-by-Step Solution: Relate torque to stress: τ_max = TR/JSet τ_max ≤ τ_allow to find T_safeTherefore, strength is indeed judged by the maximum torque safely transmitted Verification / Alternative check: Design codes specify allowable shear stress or failure theories; solving for T gives torque capacity, directly reflecting strength. Why Other Options Are Wrong: No: ignores the fundamental torsional stress relation. Only for hollow shafts: applies to both solid and hollow (with respective J). Only when angle of twist is zero: unrealistic and not a strength criterion. Depends only on length: length affects rigidity (θ), not the stress capacity directly. Common Pitfalls: Confusing strength (stress) with rigidity (twist); both must be checked, but strength is evaluated via torque capacity. Final Answer: Yes

Question 13

Combined loading — maximum normal stress for a member under direct tensile stress σx and in-plane shear τxy: Find the expression for the maximum principal (normal) stress.

Accepted Answer

Introduction: Plane stress transformation is fundamental for components under combined normal and shear actions. Determining the maximum principal stress ensures safe design against tensile failure modes. Given Data / Assumptions: Plane stress with σy = 0 (uniaxial σx) and in-plane shear τxy. Linear elasticity; small strains. Concept / Approach: The principal stresses are the eigenvalues of the 2D stress tensor. For σy = 0, the closed-form expression yields symmetric shift about σx/2 with a radius depending on τxy. Step-by-Step Solution: General principal stress: σ_{1,2} = (σx + σy)/2 ± sqrt(((σx − σy)/2)^2 + τxy^2)With σy = 0: σ_{1,2} = σx/2 ± sqrt((σx/2)^2 + τxy^2)Therefore, maximum normal stress: σ_max = σx/2 + sqrt((σx/2)^2 + τxy^2) Verification / Alternative check: Mohr's circle: center at σx/2, radius sqrt((σx/2)^2 + τxy^2); the rightmost point is σ_max as stated. Why Other Options Are Wrong: sqrt(σx^2 + 4τxy^2): incorrect combination; ignores the mid-value shift. σx + τxy or σx/2 + τxy: dimensional mixing and incorrect transformation. σx: neglects shear completely. Common Pitfalls: Forgetting σy term structure; sign conventions for τxy; misreading Mohr's circle center and radius. Final Answer: σ_max = σx/2 + sqrt((σx/2)^2 + τxy^2)

Question 14

Euler buckling of columns — determine the constant C for end conditions: According to Euler's column theory, the crippling load is P = π^2EI/(Cl^2). What is C for a column with both ends hinged (pinned-pinned)?

Accepted Answer

Introduction: Euler buckling predicts the elastic critical load for slender columns. The end conditions enter via the effective length factor through C (or K). Given Data / Assumptions: Slender, perfectly straight column; elastic material, small deflections up to buckling. Both ends hinged (pinned). Concept / Approach: For end conditions, the effective length Le modifies the denominator: Pcr = π^2EI/(Le^2). Writing Pcr = π^2EI/(Cl^2) implies C = (l/Le)^2. Step-by-Step Solution: Pinned-pinned: Le = lTherefore C = (l/Le)^2 = 1 Verification / Alternative check: Known table: pinned-pinned K = 1 ⇒ Le = l ⇒ Pcr = π^2EI/l^2, matching C = 1. Why Other Options Are Wrong: 1/4 or 1/2 or 2 or 4 correspond to other end conditions (e.g., fixed-free, fixed-pinned, fixed-fixed) and not pinned-pinned. Common Pitfalls: Mixing K (effective length factor) with C; forgetting which boundary conditions give which Le. Final Answer: 1

Question 15

Simply supported beam with a triangularly varying load: Load varies linearly from zero at support B to w per unit length at support A over span l. What is the shear force at B (i.e., reaction at B)?

Accepted Answer

Introduction: Triangularly distributed loads produce resultant forces equal to the triangle area and act at one-third from the larger-intensity end. This problem checks equilibrium and load-resultant concepts. Given Data / Assumptions: Simply supported beam; span l. w at A, zero at B (linear variation). Statics; small deflection effects ignored. Concept / Approach: Replace the triangular load with its single resultant W and its line of action. Use moment equilibrium about a support to compute reactions. Step-by-Step Solution: Resultant magnitude: W = (1/2)wlLocation: from the higher-intensity end (A) at l/3Taking moments about A: R_Bl = W*(l/3) = (wl/2)(l/3) = wl^2/6Therefore R_B = wl/6 Verification / Alternative check: Sum of vertical forces: R_A + R_B = W = wl/2; with R_B = wl/6 ⇒ R_A = wl/3 (consistent). Why Other Options Are Wrong: wl/3 or 2wl/3 or wl/2 or wl: do not satisfy both force and moment equilibrium for this load pattern. Common Pitfalls: Placing the resultant at midspan; forgetting it lies at one-third from the larger load end; mixing up which end has intensity w. Final Answer: w*l/6

Question 16

Basic definitions — identify the modulus: The ratio of linear (normal) stress to linear strain is called what?

Accepted Answer

Introduction: Material constants relate stress to strain under specific modes of deformation. This question asks for the name of the constant connecting normal stress to normal strain in uniaxial loading. Given Data / Assumptions: Small strains; linear elastic behavior. Uniaxial (normal) stress and corresponding normal strain. Concept / Approach: Hooke’s law for normal loading: σ = E*ε, where E is Young’s (modulus of elasticity). Different moduli exist for shear (G) and volumetric change (K). Step-by-Step Solution: Identify ratio: σ/εBy definition: E = σ/ε for linear elasticityHence, the required term is modulus of elasticity (Young’s modulus) Verification / Alternative check: Dimensional reasoning: [stress]/[strain] reduces to pressure units, as does E. Why Other Options Are Wrong: Modulus of rigidity: relates shear stress to shear strain (G = τ/γ). Bulk modulus: relates hydrostatic pressure to volumetric strain (K = p/ε_v). Poisson’s ratio: relates lateral to longitudinal strain, dimensionless. Shear compliance: not the requested linear modulus. Common Pitfalls: Confusing E with G or K; mixing up normal vs shear vs volumetric responses. Final Answer: modulus of elasticity

Question 17

Cantilever with end load — location of failure under increasing load: When a vertical cantilever beam carries a load at its free end, where does failure initiate as the load is increased?

Accepted Answer

Introduction: Bending failure typically initiates where bending moment is maximum. For a cantilever with an end load, recognizing the bending moment distribution is key. Given Data / Assumptions: Cantilever of length l; point load at the free end. Linear elastic behavior up to failure. Concept / Approach: Maximum bending moment occurs at the fixed support for a cantilever with end load. Extreme fiber stress is largest there, so yielding/crack initiation starts at the fixed end section. Step-by-Step Solution: Shear diagram: constant along span; bending moment varies linearly from 0 at free end to Pl at fixed endMaximum σ_bending at fixed end: σ = Mc/ITherefore, failure initiates at the fixed end Verification / Alternative check: Comparative check of stress magnitudes along the beam confirms the fixed section is critical. Why Other Options Are Wrong: Free end / middle / 2l/3: bending moment is smaller away from the fixed support. Uniformly along the span: bending stresses are not uniform. Common Pitfalls: Confusing maximum deflection (free end) with maximum bending stress (fixed end). Final Answer: at the fixed end

Question 18

Elongation of a conical bar due to its own weight: A conical bar of length l has base diameter d at the fixed upper end and tapers linearly to a point at the free lower end. Weight per unit volume is w. Find the total elongation under self-weight (a…

Accepted Answer

Introduction: Members with variable cross-section exhibit nonuniform stress under self-weight. A conical bar fixed at the large end and tapering to zero at the free tip has a neat closed-form elongation independent of base diameter. Given Data / Assumptions: Length l; base diameter d at the fixed top; linear taper to zero at bottom. Specific weight (weight per unit volume) w; Young’s modulus E. Small strains; linear elasticity. Concept / Approach: At a section x measured from the fixed end, area A(x) decreases linearly, and the axial force equals the weight of the segment below. Strain is σ/E, and total elongation is the integral of strain over the length. Step-by-Step Solution: Let A0 = πd^2/4; A(x) = A0*(1 − x/l)^2Weight below section: P(x) = w*∫_x^l A(ξ)dξ = wA0l*(1 − x/l)^3/3Stress: σ(x) = P(x)/A(x) = (wl/3)(1 − x/l)Strain: ε(x) = σ(x)/E = (wl/(3E))(1 − x/l)Elongation: δ = ∫_0^l ε(x) dx = (wl/(3E))∫_0^l (1 − x/l) dx = wl^2/(6E) Verification / Alternative check: The result is independent of d because both P(x) and A(x) scale with A0 and cancel. Dimensional check: w has units of force/volume; multiplying by l^2/E gives length. Why Other Options Are Wrong: wl^2/(2E) or /(3E): overestimates elongation; incorrect integration factors. wl/(6E): missing one power of l from the integral. wl^3/(6Ed^2): introduces d dependance that cancels in a true conical taper to a point. Common Pitfalls: Setting up A(x) incorrectly; forgetting that the line of action for self-weight is the weight of the portion below the section; missing the linear taper square in area. Final Answer: δ = wl^2/(6E)

Question 19

Helical Springs — Effect of Wire Diameter on Stiffness Two closely coiled helical springs 'A' and 'B' are identical in mean coil diameter, number of active turns, material, and overall geometry. However, the wire diameter of spring 'A' is exactly do…

Accepted Answer

Introduction: Helical spring stiffness depends strongly on wire diameter. This question checks whether you recall the correct proportionality and can compare two otherwise identical springs when the wire diameter changes. Given Data / Assumptions: Springs A and B are closely coiled and identical in material, mean coil diameter, and number of active turns. Wire diameter of A is double that of B. Linear stiffness k is load/deflection in the elastic range. Concept / Approach: For a closely coiled helical spring in shear: k = (G * d^4) / (8 * D^3 * n) where G is shear modulus, d is wire diameter, D is mean coil diameter, n is active turns. Holding G, D, n constant, stiffness is proportional to d^4. Step-by-Step Solution: Let d_B = d. Then d_A = 2d.k_A / k_B = (d_A^4) / (d_B^4) = (2d)^4 / d^4 = 16.Therefore k_B = k_A / 16. Verification / Alternative check: Doubling d massively increases stiffness because polar resistance rises with d^4. A factor of 16 is consistent with this strong dependence. Why Other Options Are Wrong: one-eighth: Implies d^3 dependence, which is incorrect. one-fourth: Would correspond to d^2 dependence. one-half: Would correspond to linear dependence on d. Common Pitfalls: Confusing spring stiffness with beam bending stiffness or misremembering the d^4 proportionality is common. Final Answer: one-sixteenth

Question 20

Combined Stress — Maximum Principal (Normal) Stress A body is under a direct tensile stress of 300 MPa in one principal plane and a simple shear stress of 200 MPa. Determine the maximum normal (principal) stress.

Accepted Answer

Introduction: This problem tests Mohr’s circle or principal stress formulas for a state with one normal stress and in-plane shear. We need the maximum principal (normal) stress. Given Data / Assumptions: σx = 300 MPa (tension), σy = 0 MPa (no perpendicular direct stress stated). τxy = 200 MPa (simple shear). Linear elasticity; plane stress condition. Concept / Approach: Principal stresses for plane stress: σ1,2 = (σx + σy)/2 ± sqrt( ((σx - σy)/2)^2 + τxy^2 ) Step-by-Step Solution: Compute the average: (σx + σy)/2 = (300 + 0)/2 = 150 MPa.Compute the radius: sqrt( ((σx - σy)/2)^2 + τxy^2 ) = sqrt( (300/2)^2 + 200^2 ) = sqrt(150^2 + 200^2 ) = sqrt(22500 + 40000) = sqrt(62500) = 250 MPa.Therefore, σ1 = 150 + 250 = 400 MPa (maximum); σ2 = 150 - 250 = -100 MPa (minimum). Verification / Alternative check: The computed pair (400 MPa, -100 MPa) preserves the invariant σ1 + σ2 = σx + σy = 300 MPa, confirming consistency. Why Other Options Are Wrong: -100 MPa: This is the minimum principal stress, not the maximum. 250 MPa: Not a principal stress here; it is the Mohr circle radius. 300 MPa: The applied direct stress, not accounting for shear transformation. Common Pitfalls: Forgetting σy = 0, misusing average vs radius, or adding magnitudes incorrectly leads to wrong answers. Final Answer: 400 MPa

Strength of Materials Questions