You are about to take up the Subsonic Aerodynamics Assessment. Please take note of the following before you take the assessment.

This assessment is timed for 60 Mins and auto submit.

Scores and correct answer will be displayed after taking up the assessment.

You can only take the assessment twice so make sure you have a strong internet connection.

All questions are required to have an answer.

This assessment is composed of 10 items multiple choice type of question.

Note to examinees: The passing score for this exam is15 points. If the score you’ve acquired is lessthan15,retakethe assessmentuntilyouacquire the passing mark.

Always remember: THINK, CHECK AND SUBMIT.

If you have any concern, please feel free to contact us.

CLASS SECTION/SCHEDULE (FRI-AM, FRI-PM, SAT-AM, SAT-PM, SUN-AM, SUN-PM, ONLINE)

1.

Where is most of the water vapor in the atmosphere can be found?

a. Tropopause b. Stratosphere c. Troposphere d. Stratopause

A

B

C

D

2.

The properties of Earth’s atmosphere which influence aircraft performance are

a. humidity and Oxygen b. humidity, temperature and pressure c. humidity, temperature, pressure and density d. Nitrogen, Oxygen, temperature and pressure

A

B

C

D

3.

It is the linear altitude corrected for gravitational effects.

a. geometric altitude b. absolute altitude c. pressure altitude d. geopotential altitude

A

B

C

D

4.

An airplane indicates a pressure of 95 kPa at takeoff, where the airport elevation is 1 km, and the temperature is 10°C. If the standard lapse rate of -5.87°C/km is assumed, at what elevation is the plane when a pressure of 75 kPa is read?

a. 1.5 km b. 3 km c. 19 km d. 20 km

A

B

C

D

5.

a. 16 psf/s b. 0.3 psf/s c. 9 psf/s d. 0.02 psf/s

A

B

C

D

6.

At a certain altitude, a standard altimeter reads 10,000 ft. If the density altitude is 8,000 ft., find the true temperature at that altitude.

a. 500 R b. 490 R c. 483 R d. 454 R

A

B

C

D

7.

a. 1082 ft. b. 1135 ft. c. 17,574 ft. d. 9, 900 ft.

A

B

C

D

8.

The difference between IAS and TAS will

a. decrease at high speeds b. increase with increasing air density c. increase with temperature decrease d. decrease with decreasing altitude

A

B

C

D

9.

Assuming ISA conditions and all other conditions are constant, if an airplane flies at the same angle of attack in straight and level flight at two different altitudes then the TAS will be

a. lower at the higher altitude b. higher at the higher altitude c. impossible to determine d. the same at both altitudes

A

B

C

D

10.

An open circuit wind tunnel draws in sea-level standard air and accelerates it through a contraction into a 1 m by 1 m test section. A differential transducer mounted in the test section wall measures a pressure difference of 45 mm of water between the inside and outside. Find the velocity in the test section.

a. 553 kph b. 186 kph c. 40 kph d. 97 kph

A

B

C

D

11.

a. 487 kPa b. 137 kPa c. 103 kPa d. 507 kPa

A

B

C

D

12.

A certain aircraft flies at the same Mach number at all altitudes. If it flies at a speed that is 120 kph slower at an altitude of 12,000 m than it does at sea level, find the Mach number at which it flies. Assume standard atmospheric conditions.

a. 0.7 b. 3.6 c. 5.5 d. 0.4

A

B

C

D

13.

An airplane is flying at a standard altitude of 16000 ft. with a velocity of 270 m/s. At a point on the wing of the airplane, the velocity is 330 m/s. Calculate the pressure at this point.

a. 82 kPa b. 48 kPa c. 35 kPa d. 79 kPa

A

B

C

D

14.

The critical angle of attack

a. alters with an increase of gross mass b. decreases as the CG moves aft c. remains the same for all masses d. increases as the CG moves forward

A

B

C

D

15.

Induced drag is decreased by

a. Wing strut b. Wing fillet c. Wing camber d. Wing fence

A

B

C

D

16.

A gas initially at a subsonic velocity enters an adiabatic diverging duct. What will happen to the velocity?

a. remains the same b. decrease c. increase d. none of the choices given

A

B

C

D

17.

If the sum of the moments of an airplane in flight is not zero, then the airplane will rotate about the

a. AC b. CG c. CP d. Neutral point

A

B

C

D

18.

In a test on an airfoil section the moment coefficient about the leading edge was found to be -0.005 at zero lift. At 6° angle of attack the moment coefficient about the leading edge was -0.240, and the lift and drag coefficients were 0.90 and 0.045 respectively. Find the position of the aerodynamic center of this airfoil section in percent of chord.

a. 0.4c b. 0.5c c. 0.6c d. none of the choices given

A

B

C

D

19.

A car windshield is 42 inches wide by 12 inches high. What horsepower is used up by the windshield at 50 miles per hour?

a. 4 b. 3.33 c. 5.27 d. 9

A

B

C

D

20.

A wing with an aspect ratio of 6 and span efficiency factor of 1 has a slope of lift curve at 0.076/degree. What is the lift coefficient at an angle of attack of 4° when the aspect ratio is 8.5? Angle of zero lift is at -2°.