Performance and Limitations + W&B

- imaginary vertical plane or line from which all measurements of arm are taken

horiziontal distance in inches from the reference datum line to the CG

product of the weight of an item multiplied by its arm
- Moment = Weight x Arm

the point at which a lever balances

weight of an empty airplane INCLUDING its unusable fuel, operating fluids, and engine oil

standard empty weight + operational equipment

total usable fuel, cargo, passengers, and drainable fuel

maxiumum allowable weight for ground operations

maximum allowable weight for takeoff

I- lift (upward force)
2- weight (gravity being downward acting force)
3 - Thrust ( forward acting force)
4- Drag ( backward acting force)

- occurs when sum of opposing forces are equal to 0
- according to Newton's 3rd Law there can be no unbalanced forces in steady flight Since the amount of force they project onto each other cancels each other out

Model based off of Bernoulli's experiment Which generates lift due to air moving over its Surface

- designed to increase velocity of airflow above its surface decreasing the pressure above the airfoil And decrease velocity at the bottom of the airfoil while increasing pressure
- this difference is what generates lift

When the pressure of a fluid decreases at points where the speed of fluid increases

- high speed flow is often associated with low pressure and vice versa

- angle between the longitudinal axis of the plane and the chord line
- measured by the angle at which the wing is attached to the fuselage
- is a fixed angle that cannot be changed by the pilot

- the direction of the airflow with respect to the wing
- when the wing moves forward and downward the relative wind will move backward and upward
- flight path and relative wind is always parallel but will always travel in opposite directions

angle between the wing chord line and the direction of the relative wind. When exceeded a stall will occur.

- as air density increases, lift/ drag increases
- is affected by pressure, temperature, and humidity

1- torque
2- gyroscopic precession
3- corkscrewing effect of the propeller slipstream
4- asymmetrical loading of the propeller (P-factor)

- applies Newton's 3rd Law (for every action there is an equal and opposite reaction)
- means that when the internal engine parts and the propeller are revolving in one direction, an equal force is trying to rotate the airplane in the opposite direction. So each time the propeller is turning clockwise, there is a equal force moving counterclockwise to try and cancel that force. The counterclockwise force is what makes the aircraft want to go to the left
- greatest when at low airspeeds with high power settings and a high angle of attack

is a left turning tendancy so some planes were made to drift left to counteract that force and create more lift on the left wing

- the resultant action or deflection of a spinning object when a force is applied to the outer rim of its rotational mass. If the access of the propeller is tilted, the resulting force exerted will be 90 degrees ahead of its direction of motion.
- most noticeable on takeoffs and in taildraggers when the tail is raised

- high speed rotation of an airplane propeller which results in the corkscrewing rotation to the slipstream as it moves rearward
- high propeller speeds and low forward speeds the slipstream strikes the vertical tail surface on the left side pushing the tail to the right and yawing the airplane to the left

- when an airplane is flying with a high AOA the bite of the downward moving propellr is greater than the bite of the upward moving propeller blade
- due to downward moving blade meeting the oncoming relative wind at a greater AOA than the upward moving blade

- is the equal and opposite reaction of the airplane to the change in direction and it acts equal and opposite to the horiziontal component of lift

is the ratio of the total load supported by the airplanes wing to the actual weight of the airplane and its contents. Expressed as the ratio of three G's
- weight of the airplane is equal to 1 G. 3 G's are the aircrafts weight x 3

- Maximum safe load factors
- Normal
- Utility
- Aerobatic

the maximum speed at which the load can be imposed on the aircraft without causing structural damage.
- increases in weight and decreases with a decrease in weight

- cause by an aggravated stall, where you exceed the critical angle of attack in combination of doing a slip and skid

- engine failure on takeoff during climbout
- crossed ontrol turn from base to final
- engine failure on approach to land
- on a go-around with full nose up trim

- close throttle
- neutralize ailerons
- apply full opposite rudder
- move elevator control forward to the neutral position
- once stall is broken spin will stop
- neutralize rudder and apply enough aft elevator pressure to return to level flight

P-ower reduced to idle
A-ilerons position to neutral
R-udder fully opposite of rotation
E-levator forward of neutral to break stall