Question 1
_______ is one of the sources of drag.
A. Viscous separation
B. Drafting
C. Signal strength
D. Lift only
View Answer
Answer: Option A
Explanation:
Viscous separation is one of the major factor of the drag generation. Drafting is concerned with drawing. Signal strength is affected by distance between source and target. Lift only is not source of drag. Lift is responsible for lift induced drag.
Question 2
Aerodynamic forces are generated due to ______________
A. shear and pressure force acting on body
B. shear effects only
C. only pressure forces
D. twisting of beam
View Answer
Answer: Option A
Explanation:
Shear force and pressure force are most fundamental cause which generates aerodynamic forces. Shear forces typically seen as resisting forces which results in friction. Pressure force or pressure gradient will generate forces as well.
Question 3
Consider an incompressible flow. If static pressure increases then, the local freestream velocity __________
A. decreases
B. increase
C. remains same
D. insufficient data
View Answer
Answer: Option A
Explanation:
If static pressure is increased then the corresponding value of the dynamic pressure should decrease. Bernoulli’s has provided better understanding of pressure acting on the aircraft.
Question 4
Drag which is produced due to lift is called?
A. Induced drag
B. Parasite drag
C. Weight
D. Thrust drag
View Answer
Answer: Option A
Explanation:
Drag which is produced due to lift is called lift induced or simply induced drag. Induced drag is generated due to downwash phenomena. This downwash induces an additional force component which is acting in the opposite direction of the aircraft forward motion. This induced force is called induced drag or lift induces drag.
Question 5
For an incompressible flow, if local area velocity decreases then, the dynamic pressure will ________
A. decrease
B. increase
C. constant
D. independent of velocity
View Answer
Answer: Option A
Explanation:
Dynamic pressure is defined as the product of density and square of velocity and 0.5. It is pressure exerted by fluid due to motion and the fluid flow. As mentioned, dynamic pressure is proportional to square of velocity and hence, if velocity decreases then, the value of corresponding dynamic pressure is reduced as well.
Question 6
For ideal flow, total pressure along streamline will be _________
A. constant
B. increases
C. decreases
D. always decreases by half
View Answer
Answer: Option A
Explanation:
Bernoulli’s theorem is one of the fundamental principles in fluid dynamics and mechanics. It stats total pressure along streamline will be constant. Total pressure is sum of static pressure and dynamic pressure.
Question 7
If I want to design an aircraft which primary flies in a low speed region then, which type of drag shouldn’t be considered?
A. Wave drag
B. Parasite drag
C. Induced drag
D. Form drag only
View Answer
Answer: Option A
Explanation:
Wave drag is drag produced at high speeds. At supersonic or near supersonic speed due to shock formation, the wave drag is produced. Hence, for low speed aircrafts, the wave drag is not a key parameter.
Question 8
If static air pressure is 0.5 bar and dynamic pressure is 0.85 bar then, find total pressure acting on a body.
A. 1.35
B. 5
C. 7
D. 8.56
View Answer
Answer: Option A
Explanation:
Total pressure = static pressure + dynamic pressure = 0.5 + 0.85 = 1.35 bar.
Question 9
Increment in the skin friction drag due to prop-wash is called _________
A. scrubbing drag
B. vortex
C. swirl
D. curling flow
View Answer
Answer: Option A
Explanation:
Scrubbing drag is drag produced due to Increment in skin friction drag as a result of prop wash. Vortex is produced due to pressure difference. Swirling is nothing but the turning of flow. Curling of flow can be seen as change in direction of flow.
Question 10
Induced drag of the airfoil is _____
A. 0.0N
B. 1.2N
C. 20 N
D. 25.8KN
View Answer
Answer: Option A
Explanation:
Given, an airfoilAirfoil has infinitely long span.Now, induced drag coefficient is given by,Cdi = S*Cl2/π*e*b2 = S*Cl2 / π*e*∞ = 0 N.
Question 11
The change in local air flow velocity will produce small change in skin friction drag.
A. True
B. False
View Answer
Answer: Option A
Explanation:
As the lift on the wing changes, the corresponding value of velocity at upper and lower surface will also change. This change in local flow velocity will produce small change at skin friction drag. This effect is called ‘super velocity’ effect.
Question 12
The location of separation point will depend on ________
A. curvature of the body
B. body weight
C. mass of body
D. only on body length
View Answer
Answer: Option A
Explanation:
Curvature of the body will affect the location of separation point.
Question 13
Wave drag is produced due to ________
A. shock wave formation
B. incompressible flow
C. fluid is not compressible
D. flow separation of incompressible flow
View Answer
Answer: Option A
Explanation:
Wave drag is primarily result of shock wave formation. Shock waves are very thin layer across which we can observe drastic change in the flow properties. Across shock, pressure and temperature will increase drastically. This sudden change in pressure results in the wave drag.
Question 14
What is interference drag?
A. Drag produced by interaction of different components
B. Skin friction drag
C. Lift induced drag
D. Drag due to weight of the aircraft only
View Answer
Answer: Option A
Explanation:
Drag produced due to interaction between various components is termed as interference drag. Skin friction drag is due to viscosity effects. Skin friction is one of the parameters which affects aerodynamic heating. Lift induced drag is result of vortices and downwash.