Aerodynamics MCQs

What is the primary cause of lift in aerodynamics? A) Thrust B) Drag C) Gravity D) Pressure difference Answer: D) Pressure difference Which law of aerodynamics states that as the speed of a fluid increases, its pressure decreases? A) Bernoulli’s principle B) Newton’s third law C) Pascal’s principle D) Boyle’s law Answer: A) Bernoulli’s principle The angle between the chord line of an airfoil and the direction of the relative airflow is known as: A) Angle of attack B) Dihedral angle C) Wing sweep angle D) Aspect ratio Answer: A) Angle of attack Which type of drag is caused by the skin friction of the airflow over the surface of an aircraft? A) Induced drag B) Parasitic drag C) Form drag D) Interference drag Answer: B) Parasitic drag The aspect ratio of a wing is defined as the ratio of its: A) Wing area to its span B) Wing chord to its span C) Wing length to its width D) Wing area to its weight Answer: A) Wing area to its span The critical Mach number is the speed at which: A) Drag becomes maximum B) Compressibility effects become significant C) Lift becomes maximum D) Stall occurs Answer: B) Compressibility effects become significant The term ‘stall’ in aerodynamics refers to: A) Loss of engine power B) Loss of lift due to exceeding critical angle of attack C) Loss of control surface effectiveness D) Excessive airframe vibration Answer: B) Loss of lift due to exceeding critical angle of attack Which of the following is an example of high-lift device used to increase the lift coefficient of an airfoil? A) Spoiler B) Rudder C) Flap D) Elevator Answer: C) Flap The circulation around an airfoil is directly related to its: A) Lift coefficient B) Drag coefficient C) Aspect ratio D) Chord length Answer: A) Lift coefficient The ratio of the aircraft’s true airspeed to the speed of sound in the surrounding air is known as the: A) Mach number B) Reynolds number C) Knudsen number D) Froude number Answer: A) Mach number Which of the following factors affects the magnitude of induced drag? A) Aspect ratio of the wing B) Air density C) Mach number D) Surface roughness Answer: A) Aspect ratio of the wing The force that acts opposite to the direction of the relative airflow and slows an aircraft down is called: A) Thrust B) Drag C) Lift D) Weight Answer: B) Drag The principle of conservation of momentum is fundamental to understanding which aspect of aerodynamics? A) Formation of shock waves B) Generation of lift C) Propagation of sound waves D) Calculation of drag Answer: B) Generation of lift The Reynolds number is used to predict the: A) Transition from laminar to turbulent flow B) Angle of attack required for lift-off C) Critical Mach number D) Maximum lift coefficient Answer: A) Transition from laminar to turbulent flow The term ‘Boundary Layer’ in aerodynamics refers to: A) The layer of air just above the troposphere B) The layer of air just below the stratosphere C) The layer of air directly adjacent to a solid surface D) The layer of air above the jet stream Answer: C) The layer of air directly adjacent to a solid surface The lift-to-drag ratio of an aircraft is a measure of its: A) Stability B) Maneuverability C) Efficiency D) Maximum speed Answer: C) Efficiency A ‘Vortex Generator’ on an aircraft wing is used to: A) Reduce drag B) Increase lift C) Stabilize the aircraft D) Improve fuel efficiency Answer: A) Reduce drag The phenomenon of ‘Ground Effect’ in aerodynamics refers to: A) Increased drag experienced by an aircraft near the ground B) Increased lift experienced by an aircraft near the ground C) Decreased drag experienced by an aircraft near the ground D) Decreased lift experienced by an aircraft near the ground Answer: B) Increased lift experienced by an aircraft near the ground In supersonic flight, the shock wave that forms around an aircraft is primarily caused by: A) Turbulent airflow B) Transonic flow C) Compressibility effects D) Boundary layer separation Answer: C) Compressibility effects The term ‘Mach Tuck’ refers to: A) Loss of control due to excessive speed B) Loss of control due to exceeding critical angle of attack C) Aerodynamic instability at high altitudes D) Sudden increase in drag during supersonic flight Answer: B) Loss of control due to exceeding critical angle of attack The ‘Wing Sweep’ on a supersonic aircraft is primarily intended to: A) Reduce form drag B) Increase induced drag C) Improve stability D) Enhance maneuverability Answer: A) Reduce form drag The term ‘Aspect Ratio’ of a wing refers to the ratio of: A) Wing area to its span B) Wing chord to its span C) Wing length to its width D) Wing area to its weight Answer: A) Wing area to its span In aerodynamics, ‘Flaps’ are used primarily to: A) Increase the aircraft’s cruise speed B) Reduce the aircraft’s stall speed C) Improve the aircraft’s range D) Enhance the aircraft’s maneuverability Answer: B) Reduce the aircraft’s stall speed The ‘Coefficient of Lift’ for an airfoil depends primarily on its: A) Angle of attack B) Aspect ratio C) Wing span D) Airspeed Answer: A) Angle of attack The phenomenon of ‘Buffeting’ experienced by an aircraft is typically caused by: A) Turbulent airflow over the wings B) Excessive lift due to high angle of attack C) Shock waves during supersonic flight D) Dynamic pressure variations Answer: A) Turbulent airflow over the wings The ‘Leading Edge Slat’ is an aerodynamic device used to: A) Increase lift B) Reduce drag C) Enhance stability D) Improve fuel efficiency Answer: A) Increase lift The ‘Center of Pressure’ on an airfoil refers to the point where: A) Lift force acts B) Weight force acts C) Drag force acts D) Thrust force acts Answer: A) Lift force acts The phenomenon of ‘Aeroelasticity’ deals with: A) Structural dynamics under aerodynamic loads B) Aerodynamic efficiency of aircraft engines C) Aerodynamic flow over curved surfaces D) Supersonic flow characteristics Answer: A) Structural dynamics under aerodynamic loads The ‘Swept Wing’ design on a jet aircraft is primarily intended to: A) Reduce drag at high speeds B) Increase lift at low speeds C) Enhance maneuverability D) Improve fuel efficiency Answer: A) Reduce drag at high speeds The ‘Coefficient of Drag’ depends primarily on the: A) Reynolds number B) Aspect ratio C) Angle of attack D) Airspeed Answer: C) Angle of attack The ‘Vortex Lift’ phenomenon is associated with: A) Low aspect ratio wings B) High aspect ratio wings C) Swept-back wings D) Delta wings Answer: D) Delta wings The phenomenon of ‘Wingtip Vortices’ is a result of: A) High-pressure air flowing over the wingtip B) Low-pressure air flowing over the wingtip C) Turbulent airflow over the wing D) Boundary layer separation near the wingtip Answer: D) Boundary layer separation near the wingtip The term ‘Aerodynamic Center’ on an airfoil is the point where the: A) Lift force is concentrated B) Weight force is concentrated C) Drag force is concentrated D) Moment remains constant Answer: D) Moment remains constantThe ‘Laminar Flow’ over an airfoil occurs when: A) Air particles move in parallel layers with minimal disruption B) Air particles move chaotically with high drag C) Turbulence increases lift D) Pressure remains constant Answer: A) Air particles move in parallel layers with minimal disruption The ‘Reynolds Number’ is a dimensionless quantity used to predict: A) Lift coefficient B) Drag coefficient C) Transition from laminar to turbulent flow D) Angle of attack Answer: C) Transition from laminar to turbulent flow The term ‘Aerodynamic Drag’ refers to the force that: A) Propels an aircraft forward B) Opposes an aircraft’s motion through the air C) Lifts an aircraft off the ground D) Stabilizes an aircraft in flight Answer: B) Opposes an aircraft’s motion through the air The ‘Center of Gravity’ of an aircraft is the point where: A) Lift force acts B) Weight force acts C) Drag force acts D) Thrust force acts Answer: B) Weight force acts The term ‘Dynamic Pressure’ in aerodynamics refers to: A) Pressure exerted by the atmosphere B) Pressure variation due to altitude C) Pressure generated by the aircraft’s speed D) Pressure inside the aircraft cabin Answer: C) Pressure generated by the aircraft’s speed The ‘Coefficient of Lift’ for an airfoil depends on: A) Angle of attack and airspeed B) Aspect ratio and wing span C) Reynolds number and Mach number D) Thrust and drag forces Answer: A) Angle of attack and airspeed The ‘Stagnation Point’ on an airfoil is where: A) Airflow velocity is zero B) Air pressure is maximum C) Boundary layer is thickest D) Vortex forms Answer: B) Air pressure is maximum The term ‘Transonic’ refers to airflow: A) Below the speed of sound B) Near the speed of sound C) Above the speed of sound D) In the stratosphere Answer: B) Near the speed of sound The ‘Prandtl-Glauert Singularity’ is associated with: A) Formation of shock waves B) Transonic airflow C) Supersonic flight D) Subsonic flight Answer: A) Formation of shock waves The ‘Thrust Reverser’ on a jet engine is used primarily to: A) Increase thrust during takeoff B) Decrease thrust during landing C) Improve fuel efficiency D) Reduce engine noise Answer: B) Decrease thrust during landing The ‘Boundary Layer Separation’ on an airfoil occurs when: A) Flow remains attached to the surface B) Flow detaches from the surface C) Lift coefficient increases D) Angle of attack decreases Answer: B) Flow detaches from the surface The ‘Swept-forward Wing’ design is primarily intended to: A) Improve high-speed stability B) Increase low-speed lift C) Reduce drag at all speeds D) Enhance maneuverability Answer: D) Enhance maneuverability The ‘Euler’s equation of motion’ in fluid dynamics describes the relationship between: A) Pressure, velocity, and potential energy B) Pressure, density, and velocity C) Density, velocity, and potential energy D) Pressure, temperature, and volume Answer: B) Pressure, density, and velocity The ‘Camber’ of an airfoil refers to its: A) Curvature of the upper and lower surfaces B) Thickness distribution along the chord C) Length from leading edge to trailing edge D) Maximum lift coefficient Answer: A) Curvature of the upper and lower surfaces The ‘Mach Cone’ is formed around an aircraft when it: A) Accelerates through the sound barrier B) Descends rapidly C) Turns at high speed D) Climbs steeply Answer: A) Accelerates through the sound barrier The ‘Kutta Condition’ in aerodynamics is related to the: A) Pressure distribution around an airfoil B) Formation of vortices at wingtips C) Transition from laminar to turbulent flow D) Generation of lift at zero angle of attack Answer: B) Formation of vortices at wingtips The ‘Jet Stream’ in the Earth’s atmosphere is a result of: A) Convective heating near the equator B) Differential heating between the poles and equator C) Coriolis effect D) Pressure variations in the troposphere Answer: B) Differential heating between the poles and equator

Aerodynamics MCQs

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