Here are Aerodynamics Fundamental board examination questions reviewer:

- Shock stall is

a. A. separation of the flow at high angles of attack and at high

Mach Numbers.

b. B. separation of the flow at the trailing edge of the wing at

high Mach Numbers.**c. C. separation of the boundary layer behind the shock wave.**

d. D. separation of the flow behind the bow wave.

Question 2

Just above the critical Mach number the first evidence of a shock

wave will appear at the

a.

A. upper side of the wing.

b. B. lower side of the wing.

c. C. leading edge of the wing.

d. D. trailing edge of the wing.

Question 3

NACA 4412 was used in the construction of the airfoil. Determine

the chord (in) if the camber equals 9.12 cm.

a. A. 22.80

b. B. 29.92**c. C. 89.76**

d. D. 228.00

Question 4

Consider an oblique shock wave with β = 35 deg and pressure ratio

of P2/P1=3. What is the upstream mach number?**a. A. 2.87**

b. B. 3.21

c. C. 4.10

d. D. 2.42

Question 5

An aircraft model is placed in a certain wind tunnel airstream. The

density of the airstream decreases to half of the original value.

The aerodynamic drag will decrease with a factor

a. A. 8.0

b. B. 1.4**c. C. 2.0**

d. D. 4.0

Question 6

A plain flap will increase CLmax by

a. A. Increasing the camber of the airfoil

b. B. Increasing angle of attack

c. C. Boundary layer control

d. D. Center of lift movement

Question 7

An elliptical planform wing has a span of 12 m and a chord of 2 m.

What is the induced drag coefficient when the lift coefficient is

0.8?**a. A. 0.034**

b. B. 0.430

c. C. 0.068

d. D. 0.860

Question 8

What is μ (slugs/ft-s) at the an altitude where the speed of sound

equals 692.662 mph?

a. A. 3.04 x 10^-7**b. B. 3.24 x 10^-7**

c. C. 3.64 x 10^-7

d. D. 3.84 x 10^-7

Question 9

The lift coefficient of an aircraft in steady horizontal flight is

0.4. Increase of angle of attack of 1 degree will increase the CL

by 0.09. A vertical up gust instantly changes the angle of attack

by 5 degrees. The load factor will be**a. A. 2.13**

b. B. 1.09

c. C. 2.00

d. D. 3.19

Question 10

To be able to predict compressibility effects, you have to

determine the**a. A. Mach Number**

b. B. EAS

c. C. TAS

d. D. IAS

Question 11

An aircraft has a stall speed of 100kt at a load factor n=1. In a

turn with a load factor of n=2, the stall speed is

a. A. 70 kt

b. B. 200 kt**c. C. 282 kt**

d. D. 141 kt

Question 12

A 5000 lb airplane with wing area of 250 sq ft and power available

of 450 hp is at flight sea level standard condition. The airplane

drag to lift relation is close to CD = 0.025 + 0.048 CL^2. At

flight speed of 180 mph, the airplane drag coefficient is *.a. A. 0.0237b. B. 0.0195c. C. 0.0206*

**d. D. 0.0278**

*Question 13To increase the critical Mach number a conventional aerofoil should*.

**_**

**a. A. have a low thickness to chord ratio**

b. B. have a large camber

c. C. be used with a high angle of attack

d. D. have a large leading edge radius

Question 14

What is the relationship of the length of a curved path, r, with

tangential velocity, v, when the strength of circulation is

constant as we move outwards from the core?

a. A. Directly Proportional

b. B. Inversely Proportional

c. C. Constant

d. D. Not related

Question 15

An aeroplane has a stall speed of 78 KCAS at its gross weight of

6,850 lbs. What is the stall speed when the weight is 5,000 lbs?

a. A. 57 KCAS**b. B. 67 KCAS**

c. C. 91 KCAS

d. D. 78 KCAS

Question 16

Given the ratio of dynamic pressure and static pressure to be

0.135, calculate the Mach number. Assume air is the medium.

a. A. 0.339**b. B. 0.439**

c. C. 0.539

d. D. 0.639

Question 17

An aircraft has a mass of 7200 kg and a wing span of 12 m. If the

wing loading is 1.968 kN/m^2, what is the induced drag when flying

at speeds of 200 knots at sea-level?

a. A. 1500 N

b. B. 1600 N**c. C. 1700 N**

d. D. 1800 N

Question 18

Regarding curved deflecting angles, what happens to the vertical

component of force as the angle of deflection increases? Assuming

that all the other parameters remain constant.**a. A. Increases**

b. B. Decreases

c. C. No relationship

d. D. Remains the same

Question 19

An aircraft is cruising at FL110. What is the ambient temperature

(K)?**a. A. 266.37**

b. B. 390.06

c. C. 479.46

d. D. 557.92

Question 20

The location of the center of pressure of a positive cambered wing

at increasing angle of attack will

a. A. Shift aft

b. B. Shift in spanwise direction**c. C. Shift forward**

d. D. Not shift

Question 21

In a two-dimensional flow pattern, where the streamlines converge

the static pressure will **_**.

a. A. not change

b. B. increase initially, then decrease**c. C. decrease**

Question 22

Two identical aeroplanes A and B are flying horizontal steady

turns. Further data are:

Condition A

W= 1500 kg

Bank= 20 deg

TAS= 130 kt

Condition B

W= 1500 kg

Bank= 20 deg

TAS= 200 kt

Which of the following statements is correct?

a. A. The load factor for A is larger than the load factor for B.

b. B. The turn radius A is larger than the turn radius B.

c. C. The lift coefficient A is smaller than the lift coefficient

B.**d. D. The rate of turn A is larger than the rate of Turn B.**

Question 23

It is the point in a fluid stream where the diameter of the stream

is the least and fluid velocity is at its maximum.

a. A. Converging-Diverging

b. B. Stagnation**c. C. Vena Contracta**

d. D. Walls

Question 24

What is the type of flow if the computed Reynolds number exceeds

4,000?

a. A. Laminar

b. B. Transient**c. C. Turbulent**

d. D. Uniform

Question 25

What force is required to push a flat plate, 3 in by 2 in at a

speed of 35 fps in a direction perpendicular to its surface?

a. A. 22.36 lbs

b. B. 11.18 lbs

c. C. 1.55 lbs**d. D. 0.078 lbs**

Question 26

On five-digit NACA airfoil, the third digit corresponds to the

camber. What does it mean if the third digit is 1.

a. A. Critical**b. B. Reflex**

c. C. Simple

d. D. Turbulent

Question 27

In supersonic flight aerofoil pressure distribution is**a. A. rectangular.**

b. B. irregular.

c. C. triangular.

d. D. the same as in subsonic flight.

Question 28

A body is placed in a certain airstream. The airstream velocity

increases by a factor 4. The aerodynamic drag will increase with a

factor **__**.

No answer provided

a. A. 12**b. B. 16**

c. C. 4

d. D. 8

Question 29

Where on the surface of a typical aerofoil will flow separation

normally start at high angles of attack?

a. A. upper side leading edge

b. B. lower side trailing edge

c. C. lower side leading edge**d. D. upper side trailing edge**

Question 30

Which among the statements about Density Altitude is incorrect?

a. A. A high density altitude will decrease the power produced by

an engine because less oxygen is available for combustion

b. B. A high density altitude requires a higher true airspeed for

takeoff and landing and will therefore increase takeoff and

landing distances

c. C. Density altitude is found by correcting pressure altitude

for temperature and humidity deviations from the standard

atmosphere**d. D. None, all statements above are correct**

Question 31

This gas law states that pressure and volume are inversely related

when the temperature is constant.

b. B. Boltzmann’s**c. C. Boyle’s**

d. D. Charles

Question 32

The flight Mach number is 0.8 and the TAS is 400 kts. What is the

speed of sound?**a. A. 500 kts**

b. B. 320 kts

c. C. 480 kts

d. D. 600 kts

Question 33

The true airspeed (TAS) is **_**.

a. A. higher than the speed of the undisturbed airstream about

the aeroplane.

b. B. equal to the IAS, multiplied by the air density at sea

level

c. C. lower than the speed of the undisturbed airstream about the

aeroplane**d. D. lower than the indicated airspeed (IAS) at ISA conditionsand altitudes below sea level**

Question 34

When the air has passed through a normal shock wave the Mach number

is

a. A. lower than before but still greater than 1.

b. B. equal to 1.

c. C. higher than before.**d. D. less than 1.**

Question 35

By what percent does the lift increase in a steady level turn at 45

degrees angle of bank, compared to straight and level flight?**a. A. 41%**

b. B. 19%

c. C. 31%

d. D. 52%

Question 36

VA is

a. A. The maximum speed at which rolls are allowed.

b. B. The speed that should not be exceeded in the climb.**c. C. The maximum speed at which maximum elevator deflection upis allowed.**

d. D. The speed at which a heavy transport aircraft should fly in

turbulence.

Question 37

Which among the following statements about symmetrical and

unsymmetrical airfoils is incorrect?

a. A. A symmetric airfoil at zero angle of attack produces

identical velocity increases and static pressure decreases on

both the upper and lower surfaces.

b. B. An unsymmetrical airfoil is able to produce an uneven

pressure distribution even at zero AOA.

c. C. The first two digits of a 4-digit airfoil will give

information whether an airfoil is unsymmetrical or not.**d. D. Because of positive camber, the area in the streamtubeabove the wing is larger than area in the streamtube below thewing and the airflow velocity above the wing is greater than thevelocity below the wing.**

Question 38

Given g = 10m/s^2, an aircraft is in a steady turn, at a constant

TAS of 300kt, and a bank angle of 45 degrees. Its turning radius is**a. A. 2381 m**

b. B. 3254 m

c. C. 4876 m

d. D. None of the above

Question 39

What is the induced drag at 100 knots of a monoplane of mass 2400

kg having a wing span of 16 m?

a. A. 632.8 N**b. B. 425.9 N**

c. C. 632.6 lbf

d. D. 425.9 lbf

Question 40

How will the density and temperature change in a supersonic flow

from a position in front of a shock wave to behind it?

a. A. Density will decrease, temperature will increase.

b. B. Density will decrease, temperature will decrease.**c. C. Density will increase, temperature will increase.**

d. D. Density will increase, temperature will decrease.

Question 41

Consider a rocket burning hydrogen and oxygen; the combustion

chamber pressure and temperature are 25 atm and 3,517 Kelvin,

respectively. The area of the rocket nozzle throat is 0.1 square

meters. The area of the exit is designed so that the exit pressure

exactly equals ambient pressure at a standard altitude of 30 km.

For the gas mixture assume that k = 1.22 and the molecular weight M

= 16. At a standard altitude of 30 km, calculate exit Mach number.**a. A. 5.21**

b. B. 1.00

c. C. 4.35

d. D. 3.56

Question 42

A stealth jet is flying at an altitude of 20km at a velocity of

2500 miles/hr. what is the mach angle.

a. A. 12.40 deg**b. B. 15.30 deg**

c. C. 6.43 deg

d. D. 18.20 deg

Question 43

The span-wise flow is caused by the difference between the air

pressure on top and beneath the wing and its direction of movement

goes from *. a. A. beneath to the top of the wing via the trailing edge *

**b. B. the top to beneath the wing via the leading edge c. **

*C. beneath to the top of the wing via the wing tip *

*d. D. the top to beneath the wing via the wing’s trailing edge *

*Question 44 *

*When the Mach number is slowly increased in straight and level flight the first shockwaves will occur *

*a. A. on the underside of the wing. *

*b. B. somewhere on the fin. *

*c. C. somewhere on the hoizontal tail. *

**d. D. at the wing root segment, upperside. **

*Question 45 *

*What is the CLmax of an aircraft with a wing loading of 700 Newtons per square meter and stalling velocity of 115 miles per hour? Assumes standard sea level conditions. *

*a. A. 0.216 *

*b. B. 0.233 *

**c. C. 0.433 **

*d. D. 0.465 *

*Question 46 *

* A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor *.

a. A. 8.0

b. B. 1.4

**c. 2**

Question 47

If a symmetrical aerofoil is accelerated from subsonic to

supersonic speed the centre of lift will move **. **

*a. A. aft to the trailing edge *

*b. B. forward to the leading edge *

*c. C. forward to the mid chord *

**d. D. aft to the mid chord **

*Question 48 *

*The Mach number *.

a. A. is the ratio between the TAS of the aeroplane and the sea

level speed of sound

b. B. is the ratio between the IAS of the aeroplane and the local

speed of sound**c. C. increases as the local speed of sound decreases**

d. D. increases at a given TAS, when the temperature rises

Question 49

How does the exterior view of an aircraft change, when the trim is

used during a speed decrease?

a. A. Elevator deflected downwards by means of a trimmable

horizontal stabilizer

b. B. Nothing changes in exterior view

c. C. The elevator is deflected further downwards by means of an

upwards deflected trimtab**d. D. The elevator is deflected upwards by means of a downwardsdeflected trimtab**

Question 50

The aircraft total drag in straight and level flight is lowest when

the

a. A. Induced drag is equal to zero

b. B. Induced drag is lowest**c. C. Parasite drag is equal to the induced drag**

d. D. Parasite drag equals 2x Cdi