Aerodynamics Mock Test 1 : Practice test for GATE Aerospace-2022 by AERO GATE TOPPER

 Aerodynamics 

Here is a quiz to help you prepare your upcoming GATE2022, ISRO, HAL exam. The GATE AE paper has several subjects, each one is equally important. However, one of the most important subjects in GATE AE is Aerodynamics. The subject is vast, but practice makes tackling it easy. 

This quiz contains important questions which match the pattern of the GATE, ISRO & HAL exams. Check your preparation level in every chapter of Aerodynamics for GATE by taking the quiz and comparing your ranks. Learn about Pitot tube, basics of aerodynamics and more! 

To know whether you have achieved the required preparation or test your time management as per the question pattern within an exam environment, join these mock test. 

Aerodynamics Mock test 1

1. Identify the type of flow which does not undergo any viscosity, surface tension nor compressibility

1. Ideal fluid
2. Real fluid
3. Newtonian fluid
4. Non-newtonian fluid

2. What will be the value of the Bulk Modulus of elasticity for an incompressible fluid is

1. Unity
2. Infinity
3. Very low
4. Zero

3. A streamlined body is one for which the

1. Skin frictio is zero
2. seperation occurs, if at all, at the farthest downstream part of the body
3. Thickness of the body is less than 1/100 of its length
4. Corners are rounded off

4. A circular cylinder 1 m diameter is plced in a uniform stream of 22 m/s. What is minimum speed of the cylinder for imminent detached stagnation

1. 420 rpm
2. 440 rpm
3. 840 rpm
4. 880 rpm

5. In case of a flow past cylinder, the location of point of seperation

1. Independent of Reynolds nummber
2. Dependent of Reynolds nummber
3. is fixed
4. can't say

6. An aircraft of 10 kN is flying at a height of 1500 m where density of air is 1.25 kg/m^3, projected area is 2 m^2 and drag coefficient is 0.008. Velocity of aircraft with respect to airis 180 kmph. Drag force will be

1. 21.2 N
2. 32.8 N
3. 25 N
4. 29.4 N

7. An aircraft of 10 kN is flying at a height of 1500 m where density of air is 1.25 kg/m^3 and lift coefficient is 0.5. Velocity of aircraft with respect to airis 180 kmph. Effective lift area of aircraft is

1. 10.8 m^2
2. 17.4 m^2
3. 12.8 m^2
4. 16.3 m^2

8. A circular cylinder of diameter 2 m is placed in a uniform flow of velocity equal to 25 m/s. For imminent detached stagnation, what should be minimum speed of cylinder in rad/sec.

1. 50
2. 25
3. 75
4. 85

9. In aeroplanes, airfoil are not kept at high angle of attack while rising because

1. Drag coefficient increase very much as angle of attack is increased
2. Seperation from trailing edge occurs
3. At high AOA BL seperates from lower surface and thus vaccum will develop below wing's lower surface
4. At angle greater than stalling angle seperation of flow occur on upper side of airfoil

10. Angle of attack is the angle between

1. Chord line and vertical axis
2. Direction of fluid flow and chord line
3. Direction of fluid flow and tangential on airfoil at the top surface
4. Direction of fluid flow and tangent at the bottom most point

11. In airfoil total drag has maximum contribution due to

1. Pressure and Form Drag
2. Form Drag
3. Pressure Drag
4. Frictional Drag

12. At very high Reynolds no. Total drag force consists of which of the following (1) Friction drag (2) Form drag

1. 1 only
2. 2 only
3. 1 and 2
4. None of these

13. At very small Reynold no. which of the following contributes in drag force (a) Friction drag (b) Pressure drag (c) Form drag

1. a and b
2. b and c
3. a and c
4. All

14. Total drag on a body is the sum of

1. Deformation drag and form drag
2. Deformation drag and frictional drag
3. Pressure drag and form drag
4. Pressure drag and frictional drag

15. Total drag force in case of immersed body depends on which of following (1) Shape of immersed body (2) Flow and fluid charecteristics

1. 1 only
2. 2 only
3. Both 1 and 2
4. Neither 1 nor 2