MOCK EXAM: Aerodynamics Pt.2 Welcome, You are about to take up the MOCK EXAM: Aerodynamics Pt.2. Please take note of the following before you take the assessment. This assessment is timed for 120 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 30 items multiple choice type of question. Always remember: THINK, CHECK AND SUBMIT. If you have any concern, please feel free to contact us. E-mail Address: assessment@flightwingsaviation.com Facebook Page: www.facebook.com/flightwingsaviation GOODLUCK! Email Adress LMS USERNAME FULL NAME CLASS SECTION/SCHEDULE (FRI-AM, FRI-PM, SAT-AM, SAT-PM, SUN-AM, SUN-PM, ONLINE) 1. It is the linear altitude corrected for gravitational effects. a. geometric altitudeb. absolute altitudec. pressure altituded. geopotential altitude A B C D 2. The properties of Earth’s atmosphere which influence aircraft performance are a. humidity and Oxygenb. humidity, temperature and pressurec. humidity, temperature, pressure and densityd. Nitrogen, Oxygen, temperature and pressure A B C D 3. 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 Rb. 490 Rc. 483 Rd. 454 R A B C D 4. The difference between IAS and TAS will a. decrease at high speedsb. increase with increasing air densityc. increase with temperature decreased. decrease with decreasing altitude A B C D 5. 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 altitudeb. higher at the higher altitudec. impossible to determined. the same at both altitudes A B C D 6. The critical angle of attack a. alters with an increase of gross massb. decreases as the CG moves aftc. remains the same for all massesd. increases as the CG moves forward A B C D 7. A gas initially at a subsonic velocity enters an adiabatic diverging duct. What will happen to the velocity? a. remains the sameb. decreasec. increased. none of the choices given A B C D 8. If the sum of the moments of an airplane in flight is not zero, then the airplane will rotate about the a. ACb. CGc. CPd. Neutral point A B C D 9. Induced drag is decreased by a. Wing strutb. Wing filletc. Wing camberd. Wing fence A B C D 10. 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 kPab. 48 kPac. 35 kPad. 79 kPa A B C D 11. What happens to the pressure across the shockwave? a. increaseb. decreasec. remains the samed. none of the above A B C D 12. It is the angle between the chord line and the longitudinal axis of the aircraft a. Sweep angleb. Angle of Attackc. Angle of Incidenced. Dihedral Angle A B C D 13. It is the angle between the chord line and the longitudinal axis of the aircraft a. Sweep angleb. Angle of Attackc. Angle of Incidenced. Dihedral Angle A B C D 14. Which of the following statements is true about maximum L/D ratio? a. can be found where Cl is at maximumb. can be found where Cd is minimumc. located where both Cl and Cd is minimumd. None of the Above A B C D 15. What happens to the value of lift as velocity is doubled? a. lift is doubledb. lift is tripledc. lift is quadrupledd. lift is reduced by half A B C D 16. 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. 0.07b. 0.08c. 0.09d. 0.10 A B C D 17. 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. 4.5b. 3.5c. 2.5d. 1.5 A B C D 18. 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? a. 173b. 273c. 373d. 473 A B C D 19. The aircraft is said to be trimmed if a. The moment at aerodynamic center is zerob. The rotation at center of pressure is zeroc. The rotation at center of gravity is zerod. The rotation at geometric center is zero A B C D 20. 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. 2132b. 1132c. 932d. 832 A B C D 21. Yaw is defined as the movement of the longitudinal axis about which axis? A. LateralB. LongitudinalC. VerticalD. Horizon A B C D 22. The net aerodynamic forces can be resolved into what two component forces? A. Lift and dragB. Weight and dragC. Thrust and dragD. Dynamic and static pressure A B C D 23. What must you do to remain in formation as your aircraft takes on fuel (increasing weight) from the tanker that is maintaining a constant altitude and true airspeed? A. Maintain a constant AOA and TASB. Decrease AOA and increase TASC. Increase AOA and maintain constant TASD. Increase AOA and TAS A B C D 24. High density altitude will: A. Decrease the power produced by an engine and increase the thrust produced by thepropeller or jetB. Increase the power produced by an engine and increase the thrust produced by thepropeller or jetC. Decrease the power produced by an engine and decrease the thrust produced by apropeller or jetD. Increase the power produced by an engine and decrease the thrust produced by thepropeller or jet A B C D 25. All motion or changes in aircraft attitude occurs about which position? A. Aerodynamic centerB. Center of pressureC. Center of gravityD. The cockpit A B C D 26. For a given altitude, what are the properties of the input provided by the static pressure port in the pitot-static system? A. The static pressure value will vary with changes in aircraft true airspeed (TAS)B. The static pressure value will vary with changes in aircraft angle of attack (AOA)C. The static pressure value will vary with changes in aircraft weightD. The static pressure value will vary with changes in atmospheric ambient static pressureand altitude A B C D 27. Two planes leave manila for southern city, a distance of 900 km. plane A travels at a ground speed of 90 kph faster than the plane B. Plane A arrives in their destination 2 hours and 15 minutes ahead of plane B. what is the ground speed of plane A? A. 205 KPHB. 315 KPHC. 240 KPHD. 287 KPH A B C D 28. When the value on the aircraft indicated airspeed (IAS) indicator equal the aircraft true airspeed (TAS) A. When static pressure at aircraft altitude is less than static pressure at sea level, on astandard dayB. When static pressure at aircraft altitude is greater than static pressure at aircraft sealevel, on a standard dayC. When static pressure at aircraft altitude equals static pressure at sea level, on astandard dayD. When static pressure at aircraft altitude equals density at sea level, on standard sealevel A B C D 29. An aircraft is climbing at a constant 350 KIAS. What change occurs in Mach number as altitude increases? A. Mach number increasesB. Mach number decreasesC. Mach number remains constantD. There is no Mach number at this speed A B C D 30. Due to friction along the connections of engine components such as gears, lobes, shafts and any mechanical transmission would tend to A. Reduce the power being transmittedB. Increase the power being transmittedC. Multiply the power being transmittedD. Nothing happen to the power being transmitted A B C D 1 out of 3