Term
|
Definition
| the rate of fuel consumption by the engine, measured in pounds per hour. |
|
|
Term
|
Definition
| The maximum amt of time that an airplane can remain airborne on a given amount of fuel. |
|
|
Term
|
Definition
| the maximum distance traveled over the gound for a given amount fuel. |
|
|
Term
|
Definition
| The angle between the horizon and the flight path of a climbing aircraft. |
|
|
Term
| Maximum AOC (angle of climb) |
|
Definition
| The climb angle that will yield the highest altitude gain in the smallest horizontal distance. Used when taking off from a short airfield or airfield surrounded by obstacles. (altitude vs. distance) |
|
|
Term
|
Definition
| The rate at which an acft gains altitude; the vertical component of velocity. |
|
|
Term
| Maximum ROC (rate of climb) |
|
Definition
| The rate that yields a maximum vertical velocity in the shortest time possible. (altitude vs time) |
|
|
Term
| Where does Max AOC for a turbojet occur? |
|
Definition
|
|
Term
| Where does Max AOC for a turboprop occur? |
|
Definition
| velocity less than L/Dmax and an AOA greater than L/DmzxAOA |
|
|
Term
| What is max AOC airspeed (Vx) for the T-34C? |
|
Definition
|
|
Term
|
Definition
| the altitude where power excess allows only 500 fpm rate of climb. |
|
|
Term
|
Definition
| the altitude at which an airplance can maintain a max roc of only 300 fpm. |
|
|
Term
|
Definition
| the altitude at which an acft can maintain a max roc of only 100 fpm. |
|
|
Term
|
Definition
| the maximum distance that can be traveled in a glide as a function of altitude, wind and lift to glide ratio. |
|
|
Term
| 3 basic types of control systems used to move the control surfaces |
|
Definition
| Conventional, power-boosted and full power. |
|
|
Term
|
Definition
| forces applied tro stick and rudder pedals transferred directly to the control surrfaces via push-pull tubes, pulleys, cables and levers. (has reversibility/gives pilot feedback) |
|
|
Term
|
Definition
| have mechanical linkages with hydraulic, pneumatic, or electrical boosters.(has some reversibility/gives some pilot feedback) |
|
|
Term
|
Definition
| "fly by wire"....the pilot has no direct connection with the control surfaces.(Not reversible/artificial means of producing pilot feedback) |
|
|
Term
|
Definition
| the use of any device used to create or enhance control feedback under various flight conditions. |
|
|
Term
|
Definition
| The initial tendency of an object to move toward or away from its original equilibrium position. |
|
|
Term
|
Definition
| The tendency of an object(airplane) to return to its state of equilibrium once disturbed from it. |
|
|
Term
| What are the two kinds of stability? |
|
Definition
|
|
Term
|
Definition
| The position with respect to time, or motion of an object after a disturbance. |
|
|
Term
| Positive dynamic stability |
|
Definition
| The initial tendency of an object to move toward its original equilibrium position after a disturbance. |
|
|
Term
| Negative static stability |
|
Definition
| The initial tendency of an object to continue moving away from its equilibrium following a disturbance. |
|
|
Term
|
Definition
| The initial tendency to accept the displacement position as a new equilibrium. |
|
|
Term
| Positive dynamic stability |
|
Definition
| When an object oscillates less and less about the equilibrium until coming to rest. (damped oscillation) |
|
|
Term
| Neutral dynamic stability |
|
Definition
| When an object socillates about the equilibrium position and does not dampen out. (undamped oscillation) |
|
|
Term
| Negative dynamic stability |
|
Definition
| When an object does not slow down but continues to climb to a higher and higher position with each oscillation and would never return to its original equilibrium position. (divergent oscillation) |
|
|
Term
|
Definition
| When the engine fails and the propeller blades stay flat to the relative wind. (the wind will drive the propeller blades around, windmilling increases the drag on the plane and adversely affects gllide performance. |
|
|
Term
|
Definition
| When the individual propeller blades are turned so they are aligned with the wind. |
|
|
Term
|
Definition
| Velocities above max endurance.(airspeed stability) |
|
|
Term
| Region of reverse command |
|
Definition
| velocities below max endurance. (airspeed instability) |
|
|
Term
| What curves determine fuel flow for a turboprop and a turbojet? |
|
Definition
| turboprop - power curves, turbojet - thrust curves. |
|
|
Term
| Define max endurance and max range |
|
Definition
| endurance = max time airborne for given amt of fuel; range = max distance over ground for given amt of fuel. |
|
|
Term
| What performance profiles occur at L/Dmax? |
|
Definition
| prop max range/jet max endurance |
|
|
Term
| What is the effect of weight on max endurance and range? |
|
Definition
|
|
Term
| What happens to max endurance and max range airspeed when weight is increased? |
|
Definition
| both airspeeds will increase. |
|
|
Term
| What is the effect of altitude on max endurance and max range? |
|
Definition
| The higher TAS and better fuel efficiency will yield an increase in range and endurance. |
|
|
Term
| What effect does a tailwind have on max range/endurance? |
|
Definition
| Increases max range and doesn't affect endurance. |
|
|
Term
| What effect does a tailwind have on max range/endurance airspeeds? |
|
Definition
| Max range airspeed will decrease, max endurance airspeed will not be affected. |
|
|
Term
| what effect does lowering the landing gear have on fuel flow at maximum endurance airspeed? |
|
Definition
| Fuel flow is greatly increased. |
|
|
Term
| Define maximum angle of climb |
|
Definition
| the angle that achieves the greatest altitude for the minimum distance covered over the ground. |
|
|
Term
| How do jets and props achieve maximum angle of climb? |
|
Definition
| Full throttle; jets at L/Dmax, props slower than L/Dmax |
|
|
Term
| Which statement is true concerning jet and prop climb performance? |
|
Definition
| Max roc angle of attack is smaller than max aoc. |
|
|
Term
| What profile should a pilot fly to clear a tall obstacle on takeoff? what airspeed is this in the T-34C? |
|
Definition
| Max Angle of Climb, 75 KIAS |
|
|
Term
| How do altitude and weight changes affect max ROC and max AOC? |
|
Definition
| increase in alt or weight will decrease excess thrust and pwr...resulting in a decreases in max roc/aoc |
|
|
Term
| What is the name for the altitude at which max pwr excess equals zero? |
|
Definition
|
|
Term
| at what aoa and velocity would you achieve max glide endurance? |
|
Definition
| at AOA greater than L/Dmax and velocity less than L/Dmax |
|
|
Term
| at what AOA and velocity would an airplane achieve max glide range: |
|
Definition
| at L/Dmax AOA and velocity. |
|
|
Term
| How do altitude, weight and headwinds affect glide performance? |
|
Definition
| Increase in alt will increase both glide range and endurance. Increase in weight decreases glide endurance but does not affect glide range. a headwind will decrease glide range and have no effect on glide endurance. |
|
|
Term
| from 10,000 ft AGL, how far could a T-34C glide with no winds? |
|
Definition
|
|
Term
| what item of contifuration will cause the greatest increase in sink rate? |
|
Definition
|
|
Term
| What are the throttle requirements in relation to airspeed in the region of reverse command? |
|
Definition
| decrease in airspeed requires an increase in throttle |
|
|
Term
| What item of configuration will cause the greatest increaes in sink rate? |
|
Definition
|
|
Term
| In the region of reverse command, what is the effect of an increase in angle of attack with no change in throttle? |
|
Definition
| If an airplane increases angle of attack without increasing the throttle, it will develop a deficit which causes either a deceleration or a descent. |
|
|
Term
| State the morion that each control surface creates. |
|
Definition
| Ailerons and spoilers are used for roll control. The rudder is used to yaw. The elevators are used for pitch control only. |
|
|
Term
| what control deflection is required to induce a nose-up pitching moment? |
|
Definition
| a nose-up pitch is created by moving the stick aft to move the elevator upward. |
|
|
Term
| What are the functions of the trim tabs? |
|
Definition
| Trimming reduces the force required to hold control surfaces in a position necessary to maintain a desired flight attitude. |
|
|
Term
| What elevator trim tab deflection is required to maintain equilibrium for a nose-up pitch attitude? |
|
Definition
| The elevator trim tab must be moved down to hold the elevator up, causing a nose-up pitch attitude. |
|
|
Term
| What provides aerodynamic balance for the rudder and elevator of the T-34C? |
|
Definition
|
|
Term
| What is responsible for mass balancing on the elevator of the T-34C? |
|
Definition
| A lead weight in the shielded horn. |
|
|
Term
| What type of controld does the T-34 use? How do cockpit control inputs move the control surfaces? |
|
Definition
| Conventional controls; stick/rudder pedals directly connected to control sfc's |
|
|
Term
|
Definition
| stability of the longitudinal axis around the lateral axis (pitch). |
|
|
Term
|
Definition
| the stability of the lateral axis around the longitudinal axis (roll) |
|
|
Term
|
Definition
| stability of ther longitudinal axis around the vertical axis (yaw) |
|
|
Term
|
Definition
| the location of the center of gravity along the longitudinal axis that would provide neutral longitudinal static stability (the aerodynamic center for the entire airplane) |
|
|
Term
|
Definition
| a condition of flight in which the reaction to a small initial sideslip results in an increase in sideslip angle. caused by negative directional static stability. |
|
|
Term
|
Definition
| occurs when an airplane has strong directional stability and weak lateral stability |
|
|
Term
|
Definition
| the result of strong lateral stability and weak directional stability. |
|
|
Term
|
Definition
| long period oscillations of altitude and airspeed while maintaining a nearly constant angle of attack. |
|
|
Term
|
Definition
| The tendency of an airplane to roll in the same direction as it is yawing. (one wing advances/one retreats which creates a diff in lift btwn 2 wings & causes airplane to roll in same direction as yaw) |
|
|
Term
|
Definition
| the tendency of an airplane to yaw away from the direction of aileron roll input. (when plane rolls upgoing wing has more lift/induced drag and retards wings forward motion causing nose to yaw in opposite direction of roll) |
|
|
Term
| Pilot Induced Oscillations |
|
Definition
| Oscillations of attitude and angle of attack caused by the pilot trying to stop unwanted aircraft oscillations, or by the instability of the control surfaces. These inputs may result in an increase in the magnitude of the original oscillations. |
|
|
Term
| How do Pilot Induced Oscillations relate to the T-34C? |
|
Definition
| the T-34C is not subject to this type of oscillation since it does not have strong longitudinal static stability. |
|
|
Term
|
Definition
| occurs in any airplane with more than one engine; when one engine fails the airplane can have directional control problems. |
|
|
Term
|
Definition
| when the propeller imparts a corkscrewing motion to the air. The corkscrewing air flows around the fuselage until it reaches the vertical stavilizer where it increases the AOA on the vertical stabilizer (can happen during high pwr/low airspeed) |
|
|
Term
|
Definition
| the yawing moment caused by one prop blade creating more thrust than the other. |
|
|
Term
| How does the T-34 compensate for torque? |
|
Definition
| it uses the elevator trim tabs to compensate for torque. |
|
|
Term
|
Definition
| a consequence of the properties of spinning objects. |
|
|
Term
|
Definition
| The angle bewteen the airplane's longitudinal axis and the relative wind, as seen from above. |
|
|
Term
|
Definition
| an aggravated stall that results in autorotation |
|
|
Term
|
Definition
| a combination of roll and yaw that propagates itself and progressively gets worse due to asymmetrically stalled wings. |
|
|
Term
| What motion does longitudinal stability concern? |
|
Definition
| the stability of the longitudinal axis around the lateral axis (pitch) |
|
|
Term
| How does the fuselage affect the longitudinal stability of an airplane? |
|
Definition
| it is a negative contributor to longitudinal static stability. |
|
|
Term
| How does the horizontal stabilizer affect the longitudinal stability of an airplane? |
|
Definition
| it is the greatest positive contributor to longitudinal static stability |
|
|
Term
| How does wing sweep affect the longitudinal stability of an airplane? |
|
Definition
| swept wings are positive contributors to longitudinal static stability. |
|
|
Term
| How does the location of the CG affect the longitudinal atability of an airplane? |
|
Definition
| If the CG is forward of the neutral point, the overall airplane has positive longitudinal stability. |
|
|
Term
| What effect does increasing wing sweep angle have on the location of the wing's aerodynamic center? |
|
Definition
| Sweeping the wing aft moves the AC aft. |
|
|
Term
| What motion does directional stability concern? |
|
Definition
| stability of longitudinal axis around vertical axis (yaw) |
|
|
Term
| What motion does lateral stability concern? |
|
Definition
| stability of lateral axis around longitudinal axis (roll) |
|
|
Term
|
Definition
| the ratio of total lift to the airplane's weight (G's) |
|
|
Term
|
Definition
| a stress-producing force that is imposed upon an airplane or component. |
|
|
Term
|
Definition
| a measure of a material's resistance to load. |
|
|
Term
|
Definition
| a measure of a material's resistance to a single application of a steadily increasing load or force. |
|
|
Term
|
Definition
| a measure of a material's ability to withstand a cyclic application of load or force |
|
|
Term
|
Definition
| the breaking or serious permanent deformation of a material due to a cyclic application of load or force. |
|
|
Term
|
Definition
| the number of applications of load or force that a component can withstand before it has the probability of failing. |
|
|
Term
|
Definition
| the greatest load factor an airplane can sustain without any risk of permanent deformation. |
|
|
Term
| What is the limit load factor of the T-34C? |
|
Definition
|
|
Term
| Where is minimum fuel flow for a turbojet found? |
|
Definition
| on the thrust required curve |
|
|
Term
| Where is mimnimum fuel flow for a turboprop found? |
|
Definition
| on the power required curve |
|
|
Term
| Maximum endurance and maximum range are both achieved in equilibrium, level flight. Where will you look to find the velocity that the airplane must fly? |
|
Definition
| the thrust required or power required curve |
|
|
Term
| Maximum endurance for the T-34C is achieved at: |
|
Definition
|
|
Term
| which is faster? max range or max endurance? |
|
Definition
|
|
Term
| what does a headwind do to max range? |
|
Definition
|
|
Term
| What does a tailwind do to max range? |
|
Definition
|
|
Term
| what do headwinds and tailwinds do to max endurance? |
|
Definition
| they have on effect on it |
|
|
Term
| What is mas rate of climb airspeed for a T-34C? |
|
Definition
|
|
Term
| What changes affect thrust and power excess and max angle of climb and max rate of climb performance? |
|
Definition
| Weight, altitude and configuration changes (landing gear/flaps)....an increase in these thing cause a decrease in Te Pe and max roc/aoc |
|
|
Term
| What is the max operating ceiling of the T-34C? |
|
Definition
|
|
Term
| What is the maximum glide range velocity for the T-34C? |
|
Definition
|
|
Term
| What is the maximum glide endurance velocity for the T-34C? |
|
Definition
|
|
