Aerodynamics 2

Question 1

DEFINE takeoff and landing airspeed in terms of stall speed

Answer 1

Takeoff Airspeed: 20% above the power off stall speed.

Landing Airspeed: 30% above stall speed

Question 2

STATE the various forces acting on an airplane during the takeoff and landing transition

Answer 2

• Rolling Friction (F_R): friction between the landing gear and the runway.
• Thrust
• Drag
• Net Accelerating Force: Thrust minus Drag and rolling friction.
• Net Decellerating Force: Drag plus Rolling Friction minus Thrust

Question 3

STATE the factors that determine the coefficient of rolling friction

Answer 3

• Runway surface
• runway condition
• tire type
• degree of brake application

Question 4

DESCRIBE the effects on takeoff and landing performance, given variations in weight, altitude, temperature, humidity, wind, and braking

Answer 4

• Weight: Increasing weight increases rolling friction, requires greater lift and a higher takeoff velocity. Doubling weight will increase takeoff distance four times.
• Increasing airfield elevation (altitude), increasing temperature, or increasing humidity will increase Density Altitude (DA). Higher DA requires a higher takeoff velocity and decreases the amount of thrust the engine can provide, thereby increasing takeoff distance.
• Braking: A decrease in braking effectiveness will incresae landing roll.

Mnemonic: “4-H Club”: High, Hot, Heavy and Humid. Whenever three or more of these are present, expect extended takeoff and landing distances.

Question 5

DESCRIBE the effects of outside air temperature (OAT) on airplane performance characteristics

Answer 5

Increasing outside air temperature increases density altitude resulting in less lift. It also decreases thrust available. It will result in a longer takeoff roll, and a lower rate of climb.

Question 6

DEFINE maximum angle of climb and maximum rate of climb profiles

Answer 6

Maximum Angle of Climb (AOC) is a comparison of altitude gained to distance traveled. Maximum vertical velocity for a minimum horizontal velocity.

Maximum Rate of Climb (ROC) is a comparison of altitude gained relative to the time needed to reach that altitude. Results in maximum vertical velocity.

Question 7

EXPLAIN the performance characteristics profiles that yield maximum angle of climb and maximum rate of climb for turboprops.

Answer 7

Maximum AOC performance depends upon thrust excess. Occurs at a velocity less than L/D_MAX and an AOA greater than L/D_MAX AOA for a turboprop

Maximum ROC performance depends upon power excess. Occurs at L/D_MAX AOA and velocity for a turboprop.

Max AOC and max ROC are not used in the T-6B. Best climb speed of 140 KIAS is used instead.

Question 8

DESCRIBE the effect of changes in weight, altitude, configuration, and wind on maximum angle of climb and maximum rate of climb profiles

Answer 8

An increase in weight, increase in altitude, lowering the landing gear, or lowering flaps will decrease max AOC and max ROC performance.

A headwind will increase AOC performance due to the decrease in groundspeed, while a tailwind will decrease AOC. Wind has no effect on ROC

Question 9

DESCRIBE the performance characteristics and purpose of the best climb profile for the T-6B,

Answer 9

Best climb speed will meet or exceed any obstacle clearance requirements while providing a greater safety margin than slower airspeeds.

Question 10

DEFINE absolute ceiling, service ceiling, cruise ceiling, combat ceiling, and maximum operating ceiling

Answer 10

Combat ceiling: Altitude where max power excess allows only 500 fpm ROC.

Cruise ceiling: altitude at which an airplane can maintain only a 300 fpm ROC.

Service ceiling: altitude at which an airplane can maintain only a 100 fpm ROC.

Absolute ceiling: The altitude at which an airplane can no longer perform a steady climb since maximum thrust excess is zero.

Operational ceiling: 31,000 ft for the T-6B

Question 11

STATE the maximum operating ceiling of the T-6B

Answer 11

31,000 ft

Question 12

STATE the relationship between fuel flow, power available, power required, and velocity for a turboprop airplane in straight and level flight

Answer 12

• Fuel flow varies directly with the power output of the engine (PA).
• Minimum fuel flow for equilibrium flight will be found on the power required (PR) curve.
• The power required curve will tell us the velocity we must fly to acheive equilibrium flight. The pilot must adjust the throttle to eliminate thrust excess.

Question 13

DEFINE maximum range and maximum endurance profiles

Answer 13

Maximum endurance is the maximum amount of time that an airplane can remain airborne on a given amount of fuel.

• Found at a velocity less than L/D_MAX and an AOA greater than L/D_MAX AOA for a turboprop.
• 8.8 units AOA for T-6B

Maximum range is the maximum distance traveled over the ground for a given amount of fuel.

• ]Found at L/D_MAX AOA for turboprops.
• 4.4 units AOA for T-6B

maximum range velocisty is faster than maximum endurance.

Question 14

EXPLAIN the performance characteristics profiles that yield maximum endurance and maximum range for turboprops

Answer 14

Maximum endurance is found at the bottom of the Power required curve for a turboprop. (a velocity less than L/D_MAX and an AOA greater than L/D_MAX AOA)

Maximum range is found at L/D_MAX AOA for turboprops in a no wind condition.

Max range airspeed would be higher than L/D max with a headwind and lower with a tailwind.

Question 15

DESCRIBE the effect of changes in weight, altitude, configuration, and wind on maximum endurance and maximum range performance and airspeed

Answer 15

• Weight: An increase in weight will decrease maximum endurance
  
  • maximum range unaffected,
  • increase max endurance and max range airspeeds.
• Altitude: max endurance and max range increases. These will also be at a higher TAS.
• Configuration: max endurance and max range will decrease when flaps or landing gear are extended.
• Wind: Headwinds will decrease maximum range while tailwinds will increase max range. Wind has no effect on maximum endurance.

Question 16

DEFINE Mach number

Answer 16

The ratio of an airplanes speed through a given air mass to sound’s speed through the same air mass.

Question 17

DEFINE critical Mach

Answer 17

The lowest mach number than an airplane can travel at and create sonic airflow somewhere on the aircraft.

Question 18

STATE the effects of altitude on Mach number and critical Mach number

Answer 18

As altitude increases, temperature decreases, resulting in a higher mach number for the same TAS. Critical Mach number will remain the same regardless of altitude.

Question 19

DEFINE maximum glide range and maximum glide endurance profiles

Answer 19

Maximum glide range is the greatest distance we can fly without an operating engine and is achieved with a minimum glide angle. L/D_MAX AOA gives us the best range velocity (V_BEST). V_BEST is 125 KIAS for the T-6B.

Maximum glide endurance is a matter of minimizing rate of descent. It is acheived at the bottom of the P_R curve, which is a lower velocity and higher AOA than L/D_MAX.

Question 20

EXPLAIN the performance characteristics profiles that yield maximum glide range and maximum glide endurance

Answer 20

L/D_{MAX<strong> </strong>}AOA and velocity will result in maximum glade range.

Maximum glide endurance velocity is less than L/D_MAX and AOA is greater than L/D_MAX AOA.

Question 21

DESCRIBE the effect of changes in weight, altitude, configuration, wind, and propeller feathering on maximum glide range and maximum glide endurance performance and airspeed

Answer 21

• Weight: An increase in weight will result in increased velocities for max glide range and max glide endurance, but the AOA will remain the same. Weight will not change the glide range, but will decrease glide endurance.
• Altitude: An increase in altitude will increase max glide range and max glide endurance of an airplane.
• Wind: A headwind will decrease max range while a tailwind will increase max range. Wind has no effect on glide endurance.
• Configuration: By extending the landing gear or flaps, the sink rate will increase and the glide range will decrease
• Propeller Feathering: Feathering the propeller result in significantly increased glide range and glide endurance over a windmilling propeller.

Question 22

DESCRIBE the locations of the regions of normal and reverse command on the turboprop power curve

Answer 22

The region of normal command for a turboprop occur at velocities greater than maximum endurance airspeed (the lowest point on the power required curve).

The region of reverse command for a turboprop occurs at velocities less than maximum endurance airspeed.

Question 23

EXPLAIN the relationship between power required and airspeed in the regions of normal and reverse command

Answer 23

In the region of normal command, more power is required for the airplane to go faster while maintaining altitude.

In the region of reverse command, more power is required for the airplane to fly at slower airspeeds and maintain altitude.

Question 24

DEFINE nosewheel liftoff/touchdown speed

Answer 24

The lowest speed that a heading and course along the runway can be maintained with full rudder and ailerons deflected when the nosewheel is off the runway; The minimum safe airspeed that the noswheel may leave the runway during takeoff, or the minimum airspeed at which the nosewheel must return to the runway during landing.

Question 25

STATE the pilot speed and attitude inputs necessary to control the airplane during a crosswind landing

Answer 25

The pilot must approach at a speed above NWLO/TD. He will maintian directional control with the rudder and apply ailerons to overcome the lateral stability that is trying to roll the airplane away from the crosswind.

Question 26

STATE the crosswind limits for the T-6B

Answer 26

Maximum crosswind component for takeoff or landing in the T-6B is 25 knots.

Question 27

DEFINE hydroplaning

Answer 27

When the airplane’s tires skim atop a thin layer of water on a runway.

Question 28

STATE the factors that affect the speed at which an airplane will hydroplane

Answer 28

The speed at which an airplane will hydroplane depends only on the tire pressures.

Question 29

DESCRIBE the effects of propeller slipstream swirl, P-factor, torque, and gyroscopic precession as they apply to the T-6B

Answer 29

• Torque will tend to roll the airplane’s fuselage counter-clockwise. Rudder and the automatic Trim Aid Device (TAD) are the primary means of compensating for engine torque.
• Propeller Factor (P-factor) is the yawing moment caused by one prop blade creating more thrust than another. It will cause the airplane to yaw right at high speeds and yaw left at low airspeeds.
• Slipstream Swirl is the corkscrew motion that the propeller imparts to the air. It causes the airplane to yaw left when at high power settings and low speeds.
• Gyroscopic Precession is a consequence of the properties of spinning objects. When a force is applied to the rim of a spinning object, a resultan force is created 90° ahead in the direction of rotation. Pitching the nose of the T-6B down causes the airplane to yaw left.

Question 30

DESCRIBE what the pilot must do to compensate for propeller slipstream swirl, P-factor, torque, and gyroscopic precession as they apply to the T-6B

Answer 30

• To compensate for torque, rudder and TAD takes over, tendency to roll a/c CCW at high power.
• To compensate for P-factor, the pilot must apply right rudder when at high power and low airspeeds and left rudder when at high power and high airspeeds.
• To compensate for slipstream swirl, the pilot must apply right rudder when at high power and low airspeeds.
• To compensate for gyroscopic precession, the pilot must apply right rudder while pitching down, and left rudder when pitching up

Question 31

DESCRIBE the effect of lift on turn performance

Answer 31

An increase in lift will result in greater turn performance by allowing an increased angle of bank.

Question 32

DESCRIBE the effect of weight on turn performance

Answer 32

Turn rate and radius are independent of weight.

Question 33

DESCRIBE the effect of thrust on turn performance

Answer 33

An airplanes thrust may limit turn performance since you must have sufficient thrust to overcome the induced drag created at high load factors.

Question 34

DESCRIBE the effect of drag on turn performance

Answer 34

Drag can limit turn performance if aircraft cannot overcome the increased induced drag.

Question 35

DEFINE turn radius and turn rate

Answer 35

Turn radius (r) is a measure of the radius of the circle the flight bath scribes.

Turn rate (ω) is the rate of heading change measured in degrees per second.

Question 36

DESCRIBE the effects of changes in bank angle on turn performance

Answer 36

Increasing bank angle will increase the turn rate and decreas the turn radius (increased turn performance)

Question 37

DESCRIBE the effects of changes in airspeed on turn performance

Answer 37

Increasing airspeed (same bank angle) would decrease the turn rate and increase turn radius (decreased turn performance)

Question 38

DESCRIBE the effects of aileron and rudder forces during turns

Answer 38

Aileron is used to set the angle of bank while rudder is used to coordinate the turn. Too much rudder in the direction of the turn will result in a skid. Opposite, or insufficient rudder the direction of the turn will result in a slip.

Question 39

EXPLAIN the aerodynamic principle that requires two G’s of backstick pressure to maintain level, constant airspeed flight, at 60 degrees angle of bank

Answer 39

In a turn, the lift vector is divided into two components, the horizontal component of lift which turns the airplane and the vertical component of lift which opposes gravity. In a level turn, the vertical component of lift must be equal to weight, therefore as bank increases, total lift must increase. at 60 degrees of bank, lift must be double weight. Load factor is equal to lift over weight (2 G).

Question 40

DESCRIBE the relationship between load factor and angle of bank for level, constant-airspeed-flight

Answer 40

Load factor increases gradually at low angles of bank, but exponentially at angles greater than 60°

Question 41

DEFINE load, load factor, limit load factor, and ultimate load factor

Answer 41

Load is a stress-producing force that is imposed upon an airplane or component.

Load factor (n) is the ratio of total lift to the airplane’s weight.

Limit Load Factor is the greatest load factor an airplane can sustain without any risk of permanent deformation.

Ultimate Load Factor is the maximum load factor that the airplane can withstand without structural failure.

Question 42

DEFINE static strength, static failure, fatigue strength, fatigue failure, service life, creep, and overstress/over-G

Answer 42

Static strength is a measure of a material’s resistance to a single application of a steadily increasing load or force.

Static failure is the breaking or serious permanent deformation of a material due to a single application of a steadily increasing load or force.

Fatigue strength is a measure of a material’s ability to withstand a cyclic application of load or force.

Fatigue failure is the breaking of a material due to a cyclic application of load or force.

Service life is the number of applications of load or force that a component can withstand before it has the probability of failing.

Creep is when a metal is subjected to high stress and temperature and it tends to stretch or elongate.

Overstress/Over-G is the condition of possible permanent deformation or damage that results from exceeding the limit load factor.

Question 43

DEFINE maneuvering speed, cornering velocity, redline airspeed, accelerated stall lines, and the safe flight envelope

Answer 43

Maneuvering speed (V_a) or cornering velocity is the indicated airspeed that an airplane can achieve its maximum turn rate and minimum turn radius. The slowest velocity that an airplane can generate its limit load. It is usually the recommended turbulent air penetration airspeed.

Redline airspeed (V_NE) is the maximum permissible airspeed for an airplane. Beyond the redline airspeed, a pilot may experience control problems and structural damage to the aircraft due to aeroelastic effects.

Accelerated stall line: a curved line describing the number of g’s that can be generated at a given indicated airspeed as a function of C_LMAX angle of attack for a particular airfoil. Also called maximum lift.

Safe flight envelope: The portion of the V-n diagram that is bounded on the left by the accelerated stall lines, on the top and bottom by the positive and negative limit loads, and on the right by redline airspeed. An aircraft may operate in its safe flight envelope without exceeding its structural or aerodynamic limits.

Question 44

DESCRIBE the boundaries of the safe flight envelope, including accelerated stall lines, limit load factor, ultimate load factor, maneuver point, and redline airspeed

Answer 44

The safe flight envelope is bounded on the left by the accelerated stall lines, on the top and bottom by the positive and negative limit loads, and on the right by redline airspeed. An aircraft may operate in its safe flight envelope without exceeding its structural or aerodynamic limits. load factor is the vertical scale, while airspeed is the horizontal scale. maneuver point is the point where the accelerated stall line and the limit load factor line intersect.

Question 45

DEFINE asymmetric loading and state the associated limitations for the T-6B

Answer 45

Assymetric loading refers to uneven production of lift on the wings of an airplane. It may be caused by a rolling pullout, trapped fuel, or hung ordnance.

Reduce Limit Load by 2/3.

In the T-6B, the maximum load factor during asymmetric loading is +4.7 to -1.0 G’s.

Question 46

DEFINE static stability and dynamic stability

Answer 46

Static stability is the initial tendency of an object to move toward or away from its equilibrium position.

Dynamic stability is the position with respect to time or motion of an object after a disturbance.

Question 47

DESCRIBE the characteristics exhibited by aircraft with positive, neutral, and negative static stabilities, when disturbed from equilibrium

Answer 47

Positive: initial tendency toward its original equilibrium position after disturbance

Neutral: initial tendency to accept the displacement position

Negative: initial tendency to continue moving away from equilibrium following a disturbance

Question 48

DESCRIBE the characteristics exhibited by aircraft with positive, neutral, and negative dynamic stabilities, when disturbed from equilibrium

Answer 48

Positive: the aircraft will tend to oscillate less over time as it returns to its original equilibrium position.

Neutral: the aircraft will continue to oscillate over time, never settling back at its original position.

Negative: the aircraft will experience greater oscilations over time.

Question 49

DESCRIBE the characteristics of damped, undamped, and divergent oscillations, and the combination of static and dynamic stabilities that result in each

Answer 49

Damped oscillation is when oscillations are reduced over time. This would result from positive static and dynamic stability.

Undamped oscillation is when the oscillations continue at the same rate and magnitude. This would result from positive static stability, but neutral dynamic stability.

Divergent Oscillation is when the oscillations grow in magnitude over time. This would result from positive static stability and negative dynamic stability.

Question 50

EXPLAIN the relationship between stability and maneuverability

Answer 50

A stable airplane will tend to be less maneuverable, while an unstable airplane will be very maneuverable.

Question 51

STATE the methods for increasing an airplane’s maneuverability

Answer 51

Maneuverabillity may be increased by decreasing stability or by giving the airplane larger control surfaces.

Question 52

STATE the effects of airplane components on an airplane’s longitudinal static stability

Answer 52

The wings having an aerodynamic center that is forward of the center of gravity decreasing longitudinal static stability.

Swept wings move the aerodynamic center aft, thus increasing its longitudinal stability

The fuselage also creates lift, and it’s aerodynamic center is generally ahead of the airplane’s CG, decreasing longitudinal static stability.

The horizontal stabilizer has an aerodynamic center far aft of the center of gravity, thus having the greatest positive effect on longitudinal stability

Question 53

EXPLAIN the criticality of weight and balance

Answer 53

The location of the center of gravity is critical to longitudinal stability. By moving cargo, ordnance, and fuel we can change the location of the center of gravity. The neutral point defines the farthest aft CG position without negative stability. With the CG ahead of the neutral point the airplane will be positively stable, but if it moves aft of the neutral point, it will become negatively stable and the pilot will have difficulty controlling it in flight.

Question 54

STATE the effects of airplane components on an airplane’s directional static stability

Answer 54

Straight wings have a small positive effect on directional static stability

Swept wings further increase directional stability

Fuselage has a negative effect on directional stability

Vertical Stabilizer is the greatest positive contributor to directional static stability

Question 55

STATE the effects of airplane components on an airplane’s lateral static stability

Answer 55

Dihedral effect of the wings is the greatest positive contributor to lateral static stability.

High-mounted wing will increase lateral stability, while a low-mounted wing decreases lateral stability.

Wing sweep also increases lateral stability

Vertical Stabilizer tends to improve lateral stability

Question 56

STATE the static stability requirements for, and the effects of, directional divergence

Answer 56

Negative directional static stability will result in directional divergence. This is a condition of flight in which the reaction to a small initial sideslip results in an increase in sideslip angle, which could cause out of control flight.

Most airplanes have very strong directional stability.

Question 57

STATE the static stability requirements for, and the effects of, spiral divergence

Answer 57

Spiral divergence occurs when an airplane has strong directional stability and weak lateral stability. If an airplane’s wing dips, directional stability will cause the airplane to yaw in that direction, developing into a tight descending spiral.

This is easily corrected by control input from the pilot.

Question 58

STATE the static stability requirements for, and the effects of, dutch roll

Answer 58

Dutch roll is the result of strong lateral stability and weak directional stability. The airplane responds to a disturbance with both roll and yaw motions that affect eachother. Appears to be “tail wagging”.

It can be tolerated and may eventually dampen out, but it is not acceptable in a figher or attack airplane when the pilot is trying to aim at a target.

Question 59

DEFINE proverse roll

Answer 59

The tendency for an airplane to roll in the same direction as it is yawing

Question 60

DEFINE adverse yaw

Answer 60

The tendency of an airplane to yaw away from the direction of aileron roll input.

Question 61

EXPLAIN how an airplane develops phugoid oscillations

Answer 61

Phugoid oscillations are long period oscillations of altitude and airspeed while maintaining a nearly constant angle of attack. For instance, an airplane struck by an upward gust of wind would gain altitude and lose airspeed, eventually when enought airspeed was lost, the airplane would nose over gaining airspeed and losing altitude. When enough airspeed was regained, the nose will pitch back up, restarting the process.

Question 62

EXPLAIN how an airplane develops pilot induced oscillations

Answer 62

Pilot induced oscillations (PIO) are short period oscillations of pitch attitude and angle of attack that occurs when a pilot is tryping to control airplane oscillations that happen over approximately the same time span as it takes to react.

When the pilots inputs coincide with the airplanes natural stability corrections the result is an over correction to each oscilltion. If the pilot releases the controls, the airplane will correct itself.

Question 63

DEFINE asymmetric thrust

Answer 63

The directional control problems experienced when one engine of a multi-engine airplane fails and creates a yawing moment toward the dead engine.

Question 64

DEFINE a spin

Answer 64

An assymetric aggrevated stall that results in autorotation.

Question 65

DEFINE autorotation

Answer 65

A combination of roll and yaw that propagates itself due to asymmetrically stalled wings.

Question 66

DESCRIBE the aerodynamic forces affecting a spin

Answer 66

Every aircraft exhibits different spin characteristics, but they all have stall and yaw about the spin axis.

If yaw is induced during a stall, it will create an AOA difference between the left and right wings, which causes the airplane to roll. This creates an even higher AOA on the downgoing wing, but reduces the AOA of the up-going wing. While both wings are stalled, they do not lose all of their lift, nor are they equally stalled. The higher the AOA on the down-going wing, the more drag it creates, creating a yawing motion about the spin axis. The combined effects of roll and yaw cause the airplane to continue its autorotation.

The spin axis is the aerodynamic axis around which stall and yaw forces act to sustain spin rotation.

The poststall gyration phase begins the instant the airplane stalls, and is where the pilot introduces yaw necessary for a spin.

The incipient stage begins after the poststall gyrations have introduced yaw and ends when the spin is fully developed. (up to two rotations)

Question 67

STATE the characteristics of erect, inverted, and flat spins

Answer 67

An Erect Spins is characterized by a nose down, upright attitude and positive Gs.

An inverted spin is characterized by an inverted attitude and negative Gs on the airplane. The position of the vertical stabilizer causes the airplane to recover easily. They are very disorienting to the aircrew and difficult to enter

A flat spin is characterized by a flat attitude and transverse “eyeball out” Gs. The control surfaces are inneffective. Cockpit indications are similar to an erect spin, except airspeed may vary.

Question 68

DESCRIBE the factors contributing to aircraft spin

Answer 68

The location of the spin axis relative to the center of gravity. Due to conservation of angular momentum, the CG closer to the spin axis results in an increased rotation rate.

Ailerons applied in the direction of spin will cause increased roll and yaw oscillations, while ailerons applied opposite of spin rotation will tend to dampen roll and yaw oscillations. Ailerons are not used to recover from a spin in a T-6B

Rudder in a spin is used to create drag, not lift, to create a yawing moment. Rudder deflected in the same direction as the spin, will result in less drag, while rudder deflected opposite the direction of the spin will create more drag, slowing the rate of rotation.

Elevator Full aft stick results in the flatest pitch attitude and the lowest spin rate, referred to as an unaccelerated spin. Any stick position other than full aft will result in a steeper pitch attitude and an increase in rotation rate, referred to as an accelerated spin.

Question 69

DISCUSS the effects of weight, pitch attitude, and gyroscopic effects on spin characteristics

Answer 69

Weight: A heavier airplane will have a slower spin entry with lesser oscillations due to its large moment of inertia. A lighter airplane will enter a spin more quickly, with greater oscillations possible, but will also recover from a spin faster.

Pitch attitude: A high pitch attitude will result in a slower spin entry with lesser oscillations due. At lower pitch attitudes, the aircraft stalls at a higher airspeed and entries are faster and more oscillatory.

Gyroscopic effects: Due to the effects of gyroscopic precession on the propeller, a T-6B in a right spin will tend to pitch down, resulting in higher rotation rate and a more oscillatory entry. In a left spin, a T-6B will tend to pitch up, having a flatter attitude, slower rotation rate and smoother entries.

Question 70

STATE how empennage design features change spin characteristics

Answer 70

The design of the vertical stabilizer and rudder and the placement of the horizontal control surfaces will significantly effect spin recovery. If airflow to the vertical fin is blocked by the horizontal surfaces, it will not be effective at stopping the autorotation. With the T-6B, the horizontal stabilizer is farther aft, exposing more of the rudder during a spin.

The T-6B also uses a dorsal fin, strakes, and ventral fins to decrease the severity of spin characteristics.

Dorsal Fin: attached to the front of the vertical stabilizer to increase its surface area. Decreases the spin rate and aids in stopping autorotation.

Ventral Fin: located beneath the empenage. Decreases the spin rate and aids in maintaining a nose-down attitude.

Strakes: located in front of the horizontal stabilizer. Increase the surface area of the horizontal stabilizer, keeping the nose pitched down and preventing a flat spin.

Question 71

STATE the cockpit indications of an erect and inverted spin

Answer 71

Erect Spin:

• Altimeter: Rapidly decreasing
• AOA: 18+ units (pegged)
• Airspeed: 120-135 KIAS
• Turn needle: pegged in direction of spin
• VSI: 6000 fpm (pegged)
• Attitude gyro: may be tumbling (60° nose down)

Inverted Spin:

• Altimeter: Rapidly decreasing
• AOA: 0 units (pegged)
• Airspeed: 40 KIAS
• Turn needle: pegged in direction of spin
• VSI: 6000 fpm (pegged)
• Attitude gyro: may be tumbling (30° nose down)

Question 72

DESCRIBE the pilot actions necessary to recover from a spin

Answer 72

1. Gear, flaps, and speed brake - Retracted
2. PCL - idle
3. Rudder - full opposite to turn needle deflection
4. Control stick - forward of neutral with ailerons neutral
5. Smoothly recover to level flight after spin rotation stops

Question 73

DESCRIBE a progressive spin

Answer 73

A progressive spin will result if, during the recovery phase, the pilot puts in full opposite rudder, but inadvertently maintains full aft stick. After one or two more spins in the initial spin direction, the nose will pitch steeply down and the airplane will snap into a reversed direction of rotation more violently than a normal spin entry.

Question 74

DESCRIBE an aggravated spin

Answer 74

An aggravated spin is caused by maintaining pro-spin rudder while moving the control stick forward of the neutral position. It is characterized by a steep nose-down pitch attitude (~70°) and an increase in spin rate (~280° per second).

Question 75

DESCRIBE wake turbulence

Answer 75

Wake turbulence is a result of the wingtip vortices formed when an airplane produces lift. Flying through wake turbulence can result in structural damage, wing stall, or compressor stall.

Question 76

DESCRIBE the effects of changes in weight, configuration, and airspeed on wake turbulence intensity

Answer 76

Weight: A heavier airplane must produce more lift to maintain level flight, and will therefore create stronger wingtip vortices.

Airspeed: Vortex strength has a direct correlation to induced drag. Since induced drag is dominant at lower airspeeds, a slower aircraft will have stronger vortices.

Configuration: If flaps are lowered, more lift is created at the wing root, which decreases the pressure differential at the wingtip.

The greatest vortex strength occurs when the airplane is heavy, slow, and clearn.

Question 77

DESCRIBE the effects of wake turbulence on aircraft performance

Answer 77

The primary hazard to aircraft is loss of control caused by induced roll. It is difficult for airplanes with short wingspans (compared to the generating airplane) to counter the induced roll.

A second hazard, called Induced flow field, is created by the interactions of both vorticed resulting in a downwash between them of up to 1500 fpm. This can be disasterous to an aircraft that is already descending at a low power setting.

Question 78

STATE the takeoff and landing interval requirements for the T-6B

Answer 78

Minimum takeoff spacing: 2 minutes behind a heavy aircraft (over 255,000 lbs) same is recommended for large aircraft

Minimum landing spacing: 3 minutes behind a heavy aircraft

Question 79

DESCRIBE procedure for wake turbulence avoidance during takeoff

Answer 79

When taking off behind a large airplane that is departing ahead of you, ensure you liftoff at least 300 feet prior to the larger airplane’s point of rotation and conduct your climb-out to remain above his flight path.

If departing after a larger aircraft has landed, plan to rotate at a point forward of where the larger aircraft’s nosewheel touched down.

Question 80

DESCRIBE procedure for wake turbulence avoidance during landing

Answer 80

When landing behind a larger airplane, stay at or above the larger airplane’s final approach path and land beyond its nosewheel touchdown point.

When landing behind a larger aircraft that has just departed, ensure that your touchdown point is prior to the large aircraft’s rotation point.

Question 81

DEFINE wind shear

Answer 81

A sudden change in wind direction or speed over a short distance in the atmosphere.

Question 82

STATE the conditions that will lead to an increasing performance wind shear

Answer 82

increase in headwind or decrease in tailwind.

Question 83

STATE the conditions that will lead to a decreasing performance wind shear

Answer 83

A tailwind, or a decrease in headwind.

Question 84

DESCRIBE the effects of wind shear on aircraft performance

Answer 84

An increasing performance wind shear will increase IAS, increase lift, and result in a steeper angle of climb when taking off.

A decreasing performance wind shear will decrease IAS, reducing lift, and resulting in a shllower angle of climb on takeoff. A rapid drop of airspeed could result in stall.

Question 85

DESCRIBE procedures for flying in and around wind shear

Answer 85

If windshear cannot be avoided in the T-6B, use these procedures in areas of suspected wind shear.

For takeoff:

1. Use the longest suitable runway. Considering crosswind, obstacles, runway surface conditions, etc.
2. Use takeoff flaps, but delay rotation (V_ROT) by the amount of predicted wind shear (up to 10 knots)
3. Rotate to normal climb attitude at increased V_ROT and maintain attitude.
4. If wind shear is encountered near V_ROT abort if possible

For Landing:

1. Set flaps to takeoff and increase approach speed by the amount of wind shear potential (up to 10 knots).
2. Establish the proper approach pitch, trim, and power setting by 1000 ft AGL. Resist the temptation to make large power reductions.
3. Remember that increasing landing speed means longer landing distances.

Question 86

DESCRIBE wind shear avoidance techniques

Answer 86

• Delay takeoff or landing until wind shear condition no longer exists.
• Consider going around if windshear is experienced during landing
• Consider diverting to another airport
• Be alert for any convective activity that might be forecast
• Visual cues include virga, localized blowing dust, rain shafts with rain diverging from the core, and any indication of lightning or tornado-like activity may indicate a microburst.
• LLWAS, NEXRAD Dopplar radar, and onboard aircraft systems may help the pilot aviod wind shear.
• PIREPS and Weather Alerts are one of the best sources of wind shear information.