AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
Description
This exam tests your understanding of aircraft structural design principles, load analysis, stress
calculations, materials, and structural components. It focuses on how aircraft structures are
designed to be strong, lightweight, and reliable while meeting safety and performance standards.
It’s ideal for Aeronautical Engineering students preparing for exams or interviews.
QUESTIONS
A design airplane has a weight of 2,200 lb and a wing area of 90 ft2. It is to be certified as
acrobatic category under FAR part 23. What is the negative limit maneuvering load factor in
which the airplane must be designed for?
a. 2.1
b. 2.5
c. 3.8
d. d. 3.0
A simply supported beam, 3 meters in length is acted upon by an upward uniformly distributed
load along its entire length with a magnitude of 8 KN/m. What is the maximum shear imposed
on the beam by the load?
a. 12 KN
,AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
b. 6 KN
c. 24 KN
d. 8 KN
A simply supported beam, 3 meters in length is acted upon by an upward uniformly distributed
load along it entire length with a magnitude 8 KN/m. What is the maximum bending moment
imposed on the sbeam by the load?
a. 9 KN-m c. 18 KN-m
b. 36 KN-m d. 6 KN-m
Structural members designed to support loadings applied perpendicular to their axes. They are
long, straight bars having a constant cross-sectional area.
a. Shafts c. Beams
b. Plates d. Bulkhead
The test pilot of a design airplane observed that if the airplane is acted upon by a strong updraft,
the airplane oscillates vertically. The airplane is:
a. Dynamically stable c. Statically and dynamically
unstable
b. Statically stable d. Statically and dynamically stable
,AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
For a given aircraft at a given condition, the limit load is constant. The ultimate load is dictated
by the factor of safety. Choose which of the following statements are CORRECT in relation to
the factor of safety and ultimate load.
a. As the factor of safety increases, the ultimate load decreases.
b. As the factor of safety increases, the ultimate load increases.
c. As the ultimate load increases, the factor of safety decreases.
d. The factor of safety is constant at 1.5 therefore, ultimate load is also constant.
Normally designed to provide restraint against rotation and all translations; therefore, reactive
forces and moments are developed along the directions where movements are not permitted.
a. Fixed support c. Roller support
b. Hinge support d. Wedge support
It is a structure composed of slender members joined together at their end points, in which the
members are subjected to only axial loads.
a. Beam structure c. Semi-monocoque structure
b. Monocoque structure d. Truss structure
Members which are loaded so that they are compressed axially and therefore have developed
within them compressive resistances or stresses.
a. Beams c. Shafts
b. Columns d. Trusses
, AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
It is a measure of the intensity of load acting on a definite plane passing through a given point in
the material.
a. Shear c. Stress
b. Torque d. Strain
The axial strain in a member is always accompanied by a lateral strain of opposite sign. Thus, if
a member stretches under load, its cross-sectional area becomes smaller at the same time. The
relationship of the lateral strain to axial strain is called:
a. Modulus ratio c. Hooke’s Law
b. Stress-strain relationship d. Poisson’s Ratio
If the skin of the wing torque box is constant at 1/16 inch and is subjected to torsional load of
2,000 ft-lb, what is the shear stress? Refer to Fig. D (see last page)
a. 1,455 psi c. 174.5 psi
b. 17,455 psi d. 14,550 psi
A design airplane intended to be certified as a commuter category under FAR part 23 has the
following specifications: design gross weight is 3,100 lb, wing span is 34 ft, MAC is 4.75 ft, and
maximum lift coefficient is 1.35 with flaps retracted. What is the required minimum cruise
speed?
a. 244 ft/s c. 144.6 ft/s
b. 166.5 ft/s d. 157.7 knots
EXAM
Description
This exam tests your understanding of aircraft structural design principles, load analysis, stress
calculations, materials, and structural components. It focuses on how aircraft structures are
designed to be strong, lightweight, and reliable while meeting safety and performance standards.
It’s ideal for Aeronautical Engineering students preparing for exams or interviews.
QUESTIONS
A design airplane has a weight of 2,200 lb and a wing area of 90 ft2. It is to be certified as
acrobatic category under FAR part 23. What is the negative limit maneuvering load factor in
which the airplane must be designed for?
a. 2.1
b. 2.5
c. 3.8
d. d. 3.0
A simply supported beam, 3 meters in length is acted upon by an upward uniformly distributed
load along its entire length with a magnitude of 8 KN/m. What is the maximum shear imposed
on the beam by the load?
a. 12 KN
,AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
b. 6 KN
c. 24 KN
d. 8 KN
A simply supported beam, 3 meters in length is acted upon by an upward uniformly distributed
load along it entire length with a magnitude 8 KN/m. What is the maximum bending moment
imposed on the sbeam by the load?
a. 9 KN-m c. 18 KN-m
b. 36 KN-m d. 6 KN-m
Structural members designed to support loadings applied perpendicular to their axes. They are
long, straight bars having a constant cross-sectional area.
a. Shafts c. Beams
b. Plates d. Bulkhead
The test pilot of a design airplane observed that if the airplane is acted upon by a strong updraft,
the airplane oscillates vertically. The airplane is:
a. Dynamically stable c. Statically and dynamically
unstable
b. Statically stable d. Statically and dynamically stable
,AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
For a given aircraft at a given condition, the limit load is constant. The ultimate load is dictated
by the factor of safety. Choose which of the following statements are CORRECT in relation to
the factor of safety and ultimate load.
a. As the factor of safety increases, the ultimate load decreases.
b. As the factor of safety increases, the ultimate load increases.
c. As the ultimate load increases, the factor of safety decreases.
d. The factor of safety is constant at 1.5 therefore, ultimate load is also constant.
Normally designed to provide restraint against rotation and all translations; therefore, reactive
forces and moments are developed along the directions where movements are not permitted.
a. Fixed support c. Roller support
b. Hinge support d. Wedge support
It is a structure composed of slender members joined together at their end points, in which the
members are subjected to only axial loads.
a. Beam structure c. Semi-monocoque structure
b. Monocoque structure d. Truss structure
Members which are loaded so that they are compressed axially and therefore have developed
within them compressive resistances or stresses.
a. Beams c. Shafts
b. Columns d. Trusses
, AERONAUTICAL DESIGN AND STRUCTURES TEST BANK
EXAM
It is a measure of the intensity of load acting on a definite plane passing through a given point in
the material.
a. Shear c. Stress
b. Torque d. Strain
The axial strain in a member is always accompanied by a lateral strain of opposite sign. Thus, if
a member stretches under load, its cross-sectional area becomes smaller at the same time. The
relationship of the lateral strain to axial strain is called:
a. Modulus ratio c. Hooke’s Law
b. Stress-strain relationship d. Poisson’s Ratio
If the skin of the wing torque box is constant at 1/16 inch and is subjected to torsional load of
2,000 ft-lb, what is the shear stress? Refer to Fig. D (see last page)
a. 1,455 psi c. 174.5 psi
b. 17,455 psi d. 14,550 psi
A design airplane intended to be certified as a commuter category under FAR part 23 has the
following specifications: design gross weight is 3,100 lb, wing span is 34 ft, MAC is 4.75 ft, and
maximum lift coefficient is 1.35 with flaps retracted. What is the required minimum cruise
speed?
a. 244 ft/s c. 144.6 ft/s
b. 166.5 ft/s d. 157.7 knots
