Airplanes and aerodyanmics

What is a slotted flap?

A slotted flap is similar to a plain flap but provides a gap between the trailing edge of the wing and the leading edge of the flap. This permits air to pass through and delays airflow seperation

The three axes of an aircraft intersect at the... A. CG B. Center of pressure C. Midpoint of the mean chord

A.

While executing a 60º level turn, your aircraft is at a load factor of 2.0. What does this mean? A. The total load on the aircraft's structure is two times its weight B. The load factor is over the load limit C. The gust factor is two times the total load limit

A. A load factor of 2.0 means the total load on an aircraft's structure is two times its weight. Because load factors are expressed in terms of Gs, a load factor of 2.0 may be spoken of as 2gs or a load factor of 4.0 as 4gs

An airplane has a normal stalling speed of 60mph but is forced into an accelerated stall at twice that speed. What max load factor will result from this maneuver? A. 4 gs B. 2 C 1

A. A rule for determine the speed at which the airplane will stall is that the stalling speed increases in proportion to the square root of the load factor. Thus, in order to force an accelerated stall at twice the normal stalling speed the load factor would have to be 4 since square root of 4 is 2

Action of the elevators moves the plane on its... A. Lateral axis B. Longitudinal axis C. Vertical axis

A. An airplane is moved about its lateral axis (pitching motion) by action of the elevators

A wing with a very high aspect ratio (in comparison with a load aspect ratio wing) will have... A. A low stall speed B. Increased drag at high AOAs C. Poor control qualities at low airpseeds

A. An increase in aspect ratio with constant velocity will decrease the drag, especially at high AOA, improving climb performance and decreasing stall speeds

The purpose of aircraft wing dihedral angle is to... A. Increase lateral stability B. Increase longitudinal stability C. Increase lift coefficient of the wing

A. Dihedral is the angle at which the wings are slanted upward from the root to the tip. When the airplane side slips slightly, one wing is forced down. Then the greater AOA on the lower wing produces increased lift, with a tendency to return the airplane to wings level flight. IE lateral stability is enhanced

During a steady climb, the angle of climb depends on.... A. Excess thrust B. Power available C. Thrust required

A. For a given weight of the airplane, the angle of climb depends on the difference between thrust and drag, or the excess thrust. The max angle of climb would occur where there exists the greatest difference between thrust available and thrust required

During a steady climb, the rate of climb depends on: A. Excess power B. Excess thrust C. Thrust available

A. For a given weight of the airplane, the rate of climb depends on the difference between the power available and the power required, or the excess power. The maximum rate would occur where there exists the greatest difference between power required and power available.

If an increase in power tends to make the nose of the airplane rise, this is the result of the.... A. Line of thrust being below the CG B. Center of lift being ahead of the CG C. Center of lift and CG being collocated

A. If an increase in power tends to make the nose of an airplane rise, it is an indication that the line of thrust is below the CG. THis combines with the changing load on the tail surfaces to create a pitch up attitude.

Which statement describes the relationship of the forces acting on an aircraft in a constant-power and constant-airspeed descent? A. Thrust is equal to drag; lift is equal to weight B. Thrust is equal to drag; weight is greater than lift C. Thrust is greater than drag; weight is greater than lift

A. In a steady flight condition, no change in speed or flight path occurs. The forces that oppose each other are also equal to each other. Lift equals weight, and thrust equals drag in a steady climb, descent, or straight and level flight

USE FIGURE 17 ON PG 39 GLEIM BOOK The airspeed indicated by point C is... A. Maneuvering speed B. Never-exceed speed C. Max structural cruising speed.

A. Point C is the maneuvering speed, or Va. it is not shown on the airspeed indicator. It is the speed below which you can move a single flight control, one time, to its full deflection, fo one axis of airplane rotation only (pitch, roll, or yaw). In smooth air, without risk of damage to the airplane. A stall will occur before the aircraft is structurally damaged.

USE FIGURE 20 PG 37 GLEIM BOOK At the airspeed represented by point A, in steady flight, the aircraft will: A. Have its maximum lift/drag ratio B. Have its minimum lift/drag ratio C. Be developing its maximum coefficient of lift

A. Points A and B both represent the airspeed at which minimum drag occurs and the maximum lift/drag occurs. That is the point at which the least power is required for both max lift and min total drag

USE FIG 21 PG 43 GLEIM BOOK Of aircraft 1,2 or 3 which has the lowest aspect ratio? A. 1 B. 2 C. 3

A. The aspect ratio is the wingspan divided by the average wing chord. Thus, 1 has the lowest aspect ratio 1= 40 \ 6= 6.6 2= 35 \ 5 =7.0 3= 48 \ 6 = 8.0

USE FIGURE 17 PG 39 GLEIM BOOK The horizontal dashed line from point C to point E represents the... A. Positive limit load factor B. Airspeed range for normal operations C. Max structural cruise airspeed range

A. The horizontal dashed line between points C and E on fig 17 is the positive limit load factor of 3.8. It indicates that structural damage may be possible when the airplane is operated beyond this limit

What type of flap creates the least change in pitching moment? Why? A. Split B. Fowler C. Slotted

A. The split flap creates the least change in pitching moment because, although it provides lift, it also results in considerably more drag than other types of flaps. Accordingly, it requires more power during approaches

When the AOA of a symmetrical airfoil is increased, the center of pressure will... A. Remain unaffected B. Have very little movement C. Move aft along the airfoil surface

A. Unlike that os an asymmetrical airfoil ( generally used in conventional wing design), the center of pressure of a symmetrical airfoil remains unaffected, regardless of AOA

When considering the forces acting upon an airplane in straight and level flight at constant airspeed, which statement is correct? A. Weight always acts vertically toward the center of the earth B. Thrust always acts forward parallel to the relative wind and is greater than drag C. Lift always acts perpendicular to the longitudinal axis of the wing and is greater than weight

A. Weight is the force that is caused by gravity accelerating the mass of the airplane and always acts vertically toward the center of the earth.

USE FIGURE 19 PG 35 IN GLEIM BOOK At which AOA does the airplane travel the max horizontal distance per foot of altitude lost? A. 6º B. 12.3º C. 20º

A. When gliding at L/Dmax the least drag is experienced at the airplane will travel the max horizontal distance per foot of altitude lost. On the charge, locate L/Dmax and drop down vertically to the bottom of the chart to determine a 6º AOA

Describe leading edge flap

Are used to maximize lift and camber of wings. This type of leading edge device is frequently used in conjunction with trailing edge flaps and can reduce the nose down pitching movement.

USE FIGURE 18 PG 40 GLEIM BOOK A 70% increase in stalling speed would imply a bank angle of.... A. 67º B. 70 C. 83

B.

Which subsonic planform provides the best lift coefficient? A. Tapered wing B. Elliptical wing C. Rectangular wing

B.

A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the... A. Wingtip providing adequate stall warning B. Wing root providing adequate stall warning C. Wingtip providing inadequate stall warning

B. A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the wing root, with the stall progression toward the wingtip, which provides adequate stall warning . Because the wingtips and the ailerons stall later, you are provided aileron control in avoiding and recovering from stall

A sweptwing airplane with weak static directional stability and increased dihedral causes an increase in... A. Mach tuck tendency B. Dutch roll tendency C. Longitudinal stability

B. A sweptwing airplane has an increase in dihedral effect is large in comparison with its static directional stability, its Dutch roll tendencies will increase

USE FIG 21 PG 43 GLEIM BOOK Consider only aspect ratio (others factors remain constant) which aircraft will generate the least drag? A. 16 B. 10 C. 9

B. Aircraft 10 has an aspect ratio of 12.6. Aircraft with the highest aspect ratio generate the least amount of drag, all other factors being constant. Thus, aircraft 10 will have the least amount of drag 16= 32 \ 5 = 6.4 10= 57 \ 4.5 = 12.66 9 = 52 \ 10.5 = 4.95

The point of an airfoil through which lift acts is the... A. Center of gravity B. Center of pressure C. Midpoint of the chord

B. Although lift is generated over the entire wing, an imaginary point is established that represents the resultant of all lift forces. This single point is the center of lift, also known as the center of pressure.

At a constant velocity in airflow, a high aspect ratio wing will have (in comparison with a low aspect ratio wing) A. Increased drag, especially at a low angle of attack B. Decreased drag, especially at a high angle of attack C. Increased drag, especially at a high angle of attack.

B. An increase in aspect ratio with constant velocity will decrease the drag, especially at high angles of attack, improving climb performance and decreasing stall speeds.

As airspeed decreases in level flight, total drag of an aircraft becomes greater than the total drag produced at the max lift/drag speed because of the.... A. Decrease in induced drag B. Increase in induced drag C. Increase in parasite drag

B. As airspeed decreases, the total drag of an aircraft becomes greater than the total drag produced at L/Dmax because of the increases in induced drag. The lower the airspeed, the greater the AOA required to produce lift to equal the sum of the downward forces and, consequently, the inducted drag will be greater.

USE FIGURE 17 ON PG 39 GLEIM BOOK What load factor would be created if positive 30 feet per second gusts were encountered at 130 MPH A. 3.8 B. 3.0 C. 2.0

B. Begin at the bottom of the figure by locating 130 mph and then move up vertically to the positive 30 feet per second diagonal line. Then move left horizontally to determine a load factor of 3.0

USE FIGURE 22 PG 47 GLEIM BOOK While rolling into a right turn, if the inclinometer appears as illustrated in C, the HCL and CF vectors would be acting on the aircraft as illustrated in... A. 3, and less right pedal B. 5, and less right pedal C. 5, and more right pedal

B. If the ball is to the left in a right turn, less right rudder is needed to center

As the angle of bank is increased, the vertical component of lift... A. Increases and the sink rate increases B. Decreases and the sink rate increases C. Increases and the sink rate decreases

B. In straight and level flight, the vertical component of lift acts directly opposite to the component of gravity or weight. Therefore, the vertical component of lift decreases. As a result, gravity is not offset by as much vertical lift, and the sink rate increases.

An aircraft wing is designed to produce life resulting from.... A. Negative air pressure below the wing's surface and positive air pressure above the wing's surface B. Positive air pressure below the wing's surface and negative air pressure above the wing's surface C. A larger center of pressure above the wing's surface and a lower center of pressure below the wing's surface

B. In the same period of time, the air flowing over the curved top of the wing must travel farther than the air flowing along the flat bottom for most wings. This means the air on the top must go faster. According to Bernoulli's principle, the pressure on the wing top decreases, resulting in a lower pressure on top of the wing and a higher pressure below this generates a lifting force over the upper curved surface of the wing in the direction of the low pressure.

Why does increasing speed also increase lift? A. The increase in velocity of the relative wind overcomes the increased drag B. The increased impact of the relative wing on an airfoil's lower surface creates a greater amount of air being deflected downward C. The increased speed of the air passing over an airfoil's upper surface increases the pressure, thus creating a greater pressure differential between the upper and lower surface

B. Increasing speed increases the air flowing over and under an airfoil. The increased impact of the relative wind on an airfoil's lower surface creates a greater amount of air being deflected downward, producing greater lift.

That portion of the aircraft's total drag created by the production of lift is called... A. Induced drag, and is not affected by the changes in airspeed B. Induced drag, and is greatly affected by changes in airspeed C. Parasite drag, and is greatly affected by changes in airspeed

B. Induced drag is the undesirable but unavoidable by product of lift and is greatly affected by changes in airspeed. The slower the airplane flies, the greater the coefficient of lift ad thus the greater the induced drag.

Airflow From two adjacent surfaces that merge and create eddy currents, turbulence, or restricted airflow is called.... A. Form drag B. Interference drag C. Skin friction drag

B. Interference drag comes from air flowing from two adjacent surfaces colliding and creating a current of turbulent air different from the original currents. Fairings and instance between lifting surfaces reduce interference drag.

USE FIGURE 22 PG 47 GLEIM BOOK While rolling into a right turn, if the inclinometer appears as illustrated in A, the HCL and CF vectors would be acting on the aircraft as illustrated in... A. 2, and more left pedal pressure is needed to center the ball B. 2, and more right pedal pressure is needed C. 4, and more right pedal pressure is needed

B. Is the ball is to the right in a right turn, right rudder is needed to center

Lift produced by an airfoil is the net force developed perpendicular to the .... A. Chord B. Relative wind C. Longitudinal axis of the aircraft

B. Lift produced by an airfoil is the net force developed perpendicular to the relative wind.

Aileron deflection moves the airplane about its... A. Lateral axis B. Longitudinal axis C. Vertical axis

B. Move about its longitudinal axis by action of the ailerons

Which relationship is correct when comparing drag and airspeed? A. Induced drag increases as the square of the airspeed B. Induced drag varies inversely as the square of the airspeed C. Profile drag varies inversely as the square of the airspeed

B. Parasite drag increases as the square of the airspeed, and induced drag varies inversely as the square of the airspeed

USE FIGURE 17 PG 39 GLEIM BOOK The airspeed indicated by point A is: A. Maneuvering speed B. Normal stall speed C. Max structural cruising speed

B. Point A is the normal stall speed Va. at this speed in the clean configuration, the airplane will stall. The normal stall speed is shown on the airspeed indicator as the low speed end of the green arc.

USE FIGURE 17 PG 39 GLEIM BOOK The airspeed indicated by point E is.... A. Maneuvering speed B. Never exceed speed C. Max structural cruising speed

B. Point E is the never exceed speed, or Vne. This airspeed is indicated on the airspeed indicator by a red line. If flight is attempted beyond Vne structural damage or failure may result from a variety of phenomena.

On which wing planform does the stall begin at the wing root and progress outward toward the wingtip? A. Sweep back wing B. Rectangular wing C. Moderate taper wing

B. Rectangular wings have a tendency to stall first at the wing root, progressing toward the wingtip. This tendency gives adequate stall warning, adequate aileron effectiveness, and leads to a wing that is usually quite stable. Rectangular wings are therefore favored in the design of low cost, low speed airplanes

The critical AOA at which a given aircraft stalls is dependent on the... A. Gross weight B. Design of the wing C. Attitude and airspeed

B. The AOA at which an aircraft stalls is dependent upon the wing design. It is a fixed number, usually an AOA between 15º and 20º

The angle between the chord line of an airfoil and the relative wind is known as the angle of... A. Lift B. Attack C. Incidence

B. The AOA is the acute angle between the chord line of the wing and the direction of the relative wind.

Aspect ratio of a wing is defined as the ratio of the... A. Wingspan to the wing root B. Wingspan to the mean chord C. Square of the chord to the wingspan

B. The aspect ratio is the ratio of the wingspan to the mean chord, not the wing root.

USE FIG 21 PG 43 GLEIM BOOK Which aircraft has the highest aspect ratio? A. 2 B. 3 C. 4

B. The aspect ratio is the wingspan divided by the average wing chord. This, aircraft 3 has the highest aspect ratio Aircraft 2= 35 \ 5 = 7.0 3= 48 \ 6 = 8.0 4= 30 \ 6 = 5.0

Max gliding distance of an aircraft is obtained when? A. Parasite drag is the least B. Induced drag and parasite drag are equal C. Induced drag equals the coefficient of lift

B. The max gliding distance of an aircraft is obtained when the total drag is at the minimum and L/D ratio is at the max. Min drag occurs when induced drag and parasite drag are equal.

If the pilot applies right rudder to a stall airplane the... A. Tail deflects right and the noise moves right B. Tail left, nose right C. Tail right, nose left

B. The rudder pedals and the rudder itself move in the same direction. By pressing the right rudder pedal on the flight deck, the pilot is causing the rudder to move to the right as well. This causes the tail to deflect to the left and the airplane to yaw to the right.

The use of a slot in the leading edge of the wing enables an airplane to land at a slower speed because it... A. Changes the camber of the wing B. Delays the stall to a higher angle of attack C. Decelerates the upper surface boundary layer air

B. The use of a slot and/or slat in the leading edge of the wing provides for the passage of air which accelerates the boundary layer on the upper surface the stall is delayed to a higher angle of attack, thus enabling the airplane to land at a slower speed.

USE FIGURE 18 PG 40 GLEIM BOOK If during a steady turn with a 50º bank, a load factor of 1.5 were imposed on an airplane which has an unaccelerated stall speed of 60 knots, at which speed would the airplane first stall? A. 68 kts B. 75 kts C 82 kts

B. Use figure to determine the percentage increase in stall speed in a steady 50º bank and a load factor of 1.5. First, find 50º angle of bank on the horizontal scale and move up vertically.

Which type of flap is characterized by large increases in lift coefficient with minimum changes in drag? A. Split B. Fowler C. Slotted

B. When extended, the Fowler flap increases the AOA, wing camber,and wing area, which provides added lift without significantly increasing drag. Thus, the Fowler flap produces large increases in lift coefficient with minimum changes in drag.

During flight with zero AOA, the pressure along the upper surface of a wing would be.... A. Equal to atmospheric pressure B. Less than atmospheric pressure C. Greater than atmospheric pressure

B. Zero AOA means that the chord line of the wing coincides with the relative wind. Because air flows a greater distance over the upper wing surface than the lower wing surface of an asymmetrical airfoil, the upper surface has a lower pressure than the lower surface.

USE FIGURE 18 PG 40 GLEIM BOOK What increases in load factor would take place if the angle of bank were increased from 60º to 80º A. 2 Gs B. 3 C. 4

C.

USE FIGURE 18 PG 40 GLEIM BOOK What is the stall speed of an airplane in a 30 degree bank turn if the level stall speed is 100 kts? A. 100 kts B. 102 C. 108

C.

USE FIGURE 18 PG 40 GLEIM BOOK What is the stall speed of an airplane under a load factor of 2 if that unaccelerated stall speed is 100 kts? A. 115 kts B. 129 C. 140zswqa

C.

USE FIGURE 18 PG 40 GLEIM BOOK What is the stall speed of an airplane under a load factor of 4 if the unaccelerated stall speed is 70 knots? A. 91 kts B. 132 C. 140

C.

A line drawn from the leading edge to the trailing edge of an airfoil and equidistant at all points from the upper and lower contours is called the... A. Chord line B. Camber line C. Mean camber line

C. A reference line drawn from the leading edge to the trailing edge that is equidistant of at all points from the upper and lower surfaces of the wing is the mean camber line

USE FIG 21 PG 43 GLEIM BOOK Consider only aspect ratio (other factors remain constant) which aircraft will generate greatest lift? A. 1 B. 2 C. 3

C. Airplanes with higher aspect ratios generate the greatest list, all other factors held constant 1= 40 \ 6 = 6.67 2= 35 \ 5 =7.0 3= 48 \ 6= 8.0

USE FIG 21 PG 43 GLEIM BOOK Consider only aspect ratio (other factors remain constant). Which aircraft will generate greatest drag? A. 1 B. 3 C. 4

C. Airplanes with the lowest aspect ratio generates the greatest drag, all other factors held constant. Thus, airplane 4 will have the greatest drag 1 = 40 \ 6 = 6.67 3= 48 \ 6 = 8.0 4 = 30 \ 6 =5.0

The AOA of a wing directly controls the... A. Angle of incidence of the wing B. Amount of airflow above and below the wing C. Distribution of positive and negative pressure acting on the wing

C. And AOA of a wing directly controls the distribution of positive and negative pressure acting on the wing by altering the speed of the airflow over the wing surfaces.

As airspeed increases in level flight, total drag of an aircraft becomes greater than the total drag produced at the max lift/drag speed because of the.... A. Increase in induced drag B. Decrease in induced drag C. Increase in parasite drag

C. As airspeed increases, the total drag of an aircraft becomes greater than the total drag produced at L/Dmax because of the increase in parasite drag

An airplane would have a tendency to nose up and have an inherent tendency to enter a stalled condition when the center of pressure is... A. Below the CG B. Aft of the CG C. Forward of the CG

C. As the AOA increases, the CP moves forward. If it moves forward of the CG it will tend to raise the noise of the airplane, thus increasing the AOA even more. This will lead to a stalled condition.

Which statement relates to Bernoulli's principle? A. For every action there is an equal and opposite reaction B. An additional upward force is generated as the lower surface of the wing deflects air downward C. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface

C. Bernoulli's principle states in part that the internal pressure of a fluid ( liquid or gas) decreases at points where the speed of the fluid increases. This same principle applies to air flowing over the curved upper surface of a wing

Changes in the center of pressure of a wing affect the aircraft's.... A. Lift/drag ratio B. Lifting capacity C. Aerodynamic balance and controllability

C. Center of pressure ( CP) is the imaginary but determinable point at which all of the upward lift forces on the wing are concentrated. In general, at high AOA the CP moves forward, while at low AOA the CP moves aft. The relationship of the CP to CG affects both aerodynamic balance and controllability

When transitioning from straight and level flight to a constant airspeed climb, the AOA and lift A. Are increased and remain at a higher lift-to-weight ratio to maintain the climb B. Remain the same and maintain a steady state lift to weight ratio during the climb C. Are momentarily increased and lift returns to a steady state during the climb

C. During the transition from straight and level flight to a climb, a change in lift occurs when back elevator pressure is first applied. Raising the aircraft's nose increases the AOA and momentarily increases the lift. Lift at this moment is now greater than weight and starts the aircraft climbing. After the flight path is stabilized on the upward incline, the AOA and lift again revert to approx the level flight values

USE FIGURE 19 PG 35 IN GLEIM BOOK. NEED TO KNOW HOW TO READ SPAGHETTI CHARTS The lift/drag at 2º AOA is approx the same as the lift/draft for.... A, 9.75º AOA B. 10.5º AOA C. 16.5º AOA

C. Enter the bottom of the chart at 2º AOA and move vertically up to the L/D curve. From this point move right horizontally until you again reach the L/D curve. Then move vertically down to the bottom of the chart to determine a 16.5º AOA. Thus, the L/D ratio is approx the same at both 2º and 16.5º

Which statement is true regarding the forces acting on an airplane in a steady state climb? A. The sum of all forward forces is greater than the sum of all rearward forces B. The sum of all upward forces is greater than the sum of all downward forces C. The sum of all upward forces is equal to the sum of all downward forces

C. In a steady flight condition, the opposing forces are equal. Thus, in a steady climb, descent, or straight and level flight, total upward forces equal total downward forces

During flight, advancing thrust will: A. Increase airspeed B. Cause the aircraft to climb C. Cause the aircraft to increase airspeed and climb

C. Increasing engine thrust will increase airspeed. As a side effect of the increased airspeed, additional lift will be produced which will in turn cause a climb.

If an airplane's gross weight is 3,250 pounds what is the load acting on this airplane during a level 60º banked turn? A. 3,250lbs B. 5,200 C. 6,500

C. Load factor is the ratio of the total load supported by the airplane's wing to the actual weight of the airplane and its contents. A level 60º bank imposes a load factor of approx 2.0. Thus imposing a load factor of 2.0 on an airplane that weighs an actual 3,250lbs would impose a wingload of 6,500lbs.

Structural damage or failure is more likely to occur in smooth air at speeds above... A. Vno B. Va C. Vne

C. Never exceed speed (Vne) is a design limi speed where load factors could be exceeded with airspeed in excess of Vne from a variety of phenomena. Operating above this speed is prohibited because it may result in damage or structural failure

USE FIGURE 17 PG GLEIM BOOK The airspeed indicated by point D is... A. Maneuvering speed B. Never exceed speed C. Max structural cruising speed

C. Point D is the max structural cruising speed, or Vno. This airspeed is indicated on the airspeed indicator by the upper limit of the green arc (or lower limit of the yellow arc). This is the max speed for normal operation

USE FIGURE 20 PG 37 GLEIM BOOK At an airspeed represented by point B, in steady flight, the pilot can expect to obtain the aircrafts.... A. Max coefficient of lift B. Min coefficient of lift C. Max glide range in still air

C. Points B and A both represent the airspeed at which min drag occurs. At this speed, the pilot can expect to obtain the aircrafts max glide range

Which type of flap creates the greatest change in pitching moment? Why? A. Plain B. Split C. Fowler

C. The Fowler flap provides the greatest amount of fit with the least amount of drag. When extended, it not only tilts downward, but slides rearward on tracks. This increases the AOA, wing camber,and wing area. Therefore, providing added lift without significantly increasing drag. This creates the greatest change in pitching moment

The angle between the chord line of the wing and the longitudinal axis of the aircraft is known as... A. Dihedral B. The AOA C. The angle of incidence

C. The angle of incidence is the acute angle formed by the chord line of the wing and the longitudinal axis of the aircraft

USE FIG 21 PG 43 GLEIM BOOK Which aircraft has the lowest aspect ratio? A. 2 B. 3 C. 4

C. The aspect ratio is the wingspan divided by the average wing chord, thus aircraft 4 has the lowest aspect ratio

USE FIGURE 19, PG 35 IN GLEIM BOOK Which statement is true regarding airplane flight at L/Dmax? A. Any angle of attack other than that for L/Dmax increases parasite drag B. Any AOA other than that for L/Dmax increases the lift/drag ratio C. Any AOA other than that for L/Dmax increases total drag for a given airplanes lift

C. The max lift/drag ratio occurs at one AOA. If the airplane is operated in steady flight at L/Dmax, the total drag is at a min. Any AOA lower or higher than that for L/Dmax reduces the lift/drag ratio and consequently increases the total drag of a given airplanes lift.

USE FIGURE 17 PG 39 GLEIM BOOK A positive load factor of 4 at 140 MPH would cause the airplane to.... A. Stall B. Break apart C. Be subjected to structural damage

C. The velocity/load factor chart has indicated airspeed on the horizontal axis and load factor on the vertical axis. Plotting a positive load factor of 4 at 140 MPH by going up the vertical axis to 4 and over to 140 shows that you would be in the shaded area, which would cause the airplane to be subjected to structural damage.

The force which imparts a change in the velocity of a mass is called... A. Work B. Power C. Thrust

C. Thrust is the force that imparts a change in the velocity of the mass. It may be measured in pounds but has no element of time or rate

Describe a fixed slot

Fixed slots direct airflow to the upper wing surface and delay airflow separation at higher AOAs

Describe a leading edge cuff

Leading edge cuffs extend the leading edge down and forward. This causes the airflow to attach better to the upper surface of the wing at higher AOAs, thus lowering an aircrafts stall speed. The fixed nature of leading edge cuffs extracts a penalty in max cruise speed, but recent advances in design and tech have reduced this penalty.

Describe a movable slot

Movable slots consist of leading edge segments, which move on tracks. At low AOAs, each slot is held flush against the wing's leading edge by the high pressure that forms there. As the AOA increases, the high pressure area moves aft below the lower surface of the wing, allowing the slots to move forward

What is a Fowler flap?

The Fowler flap, when extended, not only tilts downwards but also slides rearward on tracks. This increases the angle of attack, wing camber, and wing area, thereby providing added lift without significantly increasing drag.

What is a split flap?

The split flap is a hinged portion of only the bottom surface of the wing. When extended, it increases the AOA by changing the chord line