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

1.

What happens to the pressure across the shockwave?

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

A

B

C

D

2.

The aircraft is said to be trimmed if

a. The moment at aerodynamic center is zero b. The rotation at center of pressure is zero c. The rotation at center of gravity is zero d. The rotation at geometric center is zero

A

B

C

D

3.

It is the angle between the chord line and the longitudinal axis of the aircraft

a. Sweep angle b. Angle of Attack c. Angle of Incidence d. Dihedral Angle

A

B

C

D

4.

Which of the following statements is true about maximum L/D ratio?

a. can be found where Cl is at maximum b. can be found where Cd is minimum c. located where both Cl and Cd is minimum d. None of the Above

A

B

C

D

5.

What happens to the value of lift as velocity is doubled?

a. lift is doubled b. lift is tripled c. lift is quadrupled d. lift is reduced by half

A

B

C

D

6.

a. 54,000 b. 44,000 c. 62, 000 d. 32,000

A

B

C

D

7.

a. 12 km b. 13 km c. 14 km d. 15 km

A

B

C

D

8.

a. 91 ft/s b. 81 ft/s c. 131 ft/s d. 241 ft/s

A

B

C

D

9.

a. 308.22 ft/s b. 542.0 ft/s c. 238.33 ft/s d. 448.6 ft/s

A

B

C

D

10.

Air enters a converging-diverging nozzle at 0.5 MPa with a negligible velocity. Assuming the flow to be isentropic, determine the pressure that will result in an exit Mach number of 1.8.

a. 0.07 b. 0.08 c. 0.09 d. 0.10

A

B

C

D

11.

An airfoil is in a freestream where P = 0.61 atm, ρ = 0.819 kg/m^3, and V = 300 m/ s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the velocity at that point.

a. 2132 b. 1132 c. 932 d. 832

A

B

C

D

12.

Consider a normal shock wave in air where the upstream flow properties are V = 680 m/s, T = 288 K, and P = 1 atm. Calculate the pressure downstream of the shock.

a. 4.5 b. 3.5 c. 2.5 d. 1.5

A

B

C

D

13.

Consider the isentropic supersonic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 10.25. The reservoir pressure and temperature are 5 atm and 600 R, respectively. Calculate the temperature at the nozzle exit.

a. 240 K b. 283 K c. 162 K d. 146 K

A

B

C

D

14.

A slender missile is flying at Mach 1.5 at low altitude. Assume the wave generated by the nose of the missile is a Mach wave. This wave intersects the ground 559 ft behind the nose. At what altitude is the missile flying?