Principles of Flight Questions

Bernoulli's principle states that in a streamline flow, an increase in velocity is accompanied by:

The continuity equation states that for an incompressible fluid in a streamtube:

The venturi effect demonstrates that as a fluid flows through a constriction:

The coefficient of lift (CL) depends primarily on:

The lift formula is L = CL × ½ρV² × S, where S represents:

As angle of attack increases from zero, lift:

The center of pressure on a conventional airfoil moves in which direction as angle of attack increases (below stall)?

The aerodynamic center of a subsonic airfoil is located at approximately:

Total drag on an aircraft is the sum of:

Induced drag is caused by:

Induced drag varies with speed such that it:

Parasite drag varies with speed such that it:

The speed at which total drag is minimum occurs when:

Skin friction drag is reduced by:

Interference drag is caused by:

Winglets reduce drag by:

The critical angle of attack is:

An aircraft always stalls at the same:

Increasing aircraft weight causes the stall speed to:

The stall speed in a 60° banked turn increases by a factor of:

Forward CG position causes the stall speed to:

Wing contamination (ice, frost, insects) affects the stall by:

Washout (wing twist) is designed to:

A deep stall is most dangerous on aircraft with:

The critical Mach number (Mcrit) is the:

Above the critical Mach number, a normal shock wave on the wing causes:

Mach tuck is:

A Mach trimmer is designed to:

The speed of sound depends on:

At sea level ISA conditions, the speed of sound is approximately:

Wing sweep delays the onset of compressibility effects by:

Supercritical airfoil sections are designed to:

Buffet onset at high speed is caused by:

The coffin corner refers to:

Static stability means that when displaced from equilibrium, the aircraft:

Dynamic stability refers to:

An aircraft can be statically stable but dynamically unstable. This means:

Longitudinal static stability is primarily provided by:

The static margin is defined as:

Moving the CG forward of its normal position makes the aircraft:

Moving the CG aft toward the neutral point:

The neutral point is the CG position at which:

Directional (weathercock) stability is primarily provided by:

Lateral static stability (tendency to return to wings-level after a roll disturbance) is enhanced by:

Dutch roll is:

The phugoid is a:

The short-period oscillation involves:

Spiral instability occurs when:

Adverse yaw is the tendency of the aircraft to yaw:

Aileron reversal at high speed occurs when:

Trailing edge flaps increase lift primarily by:

Fowler flaps are the most effective flap type because they:

Leading edge slats increase CLmax by:

Deploying flaps generally increases:

Krueger flaps are:

Leading edge slots (fixed) work by:

Propeller blade angle is the angle between:

A constant-speed propeller maintains RPM by:

Propeller feathering means:

Asymmetric blade effect (P-factor) causes:

Gyroscopic precession of a propeller causes:

Slipstream (spiraling) effect from a clockwise-rotating propeller (viewed from cockpit) tends to yaw the aircraft:

Propeller torque effect causes:

A spin is an autorotation resulting from:

Standard spin recovery procedure (most aircraft) is:

The incipient phase of a spin is:

Aft CG affects spin recovery by:

Ground effect reduces:

Ground effect is significant when the aircraft is within approximately:

When entering ground effect during landing, the aircraft tends to:

Load factor (n) is defined as:

In a 45° banked level turn, the load factor is:

In a 60° banked level turn, the load factor is:

The V-n diagram (flight envelope) shows:

VA (maneuvering speed) is the speed at which:

VA decreases when aircraft weight:

A high aspect ratio wing produces:

Wing dihedral provides:

Anhedral (negative dihedral) is used on some aircraft to:

Increasing wing sweep angle at constant area will:

Vortex generators on a wing surface are used to:

A wing fence (chordwise fence) is used to:

Form drag is caused by:

The boundary layer transitions from laminar to turbulent due to:

A turbulent boundary layer compared to a laminar boundary layer has:

Downwash behind a wing is:

The downwash angle affects the tailplane by:

Stall warning is required to occur:

In icing conditions, the stall speed:

VMO/MMO is:

Wave drag appears at transonic speeds due to:

Dihedral effect (Clβ) is a measure of:

Frise ailerons reduce adverse yaw by:

Taking off in ground effect can be hazardous because:

The limit load factor for a normal category aircraft is:

The ultimate load factor is:

Bernoulli's equation is strictly valid for:

Circulation theory (Kutta-Joukowski) states that lift per unit span equals:

An oblique shock wave differs from a normal shock wave in that:

An elliptical lift distribution on a wing produces: