Term
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Definition
| Represents only magnitude |
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Term
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Definition
| Represents magnitude and direction. Used to represent displacement, velocity, acceleration, or force. |
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Term
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Definition
| A push or pull exerted on a body. Force = Mass x Acceleration |
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Term
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Definition
| Quantity of molecular material that comprises an object. |
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Term
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Definition
| Amout of space occupied by an object. |
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Term
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Definition
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Term
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Definition
| Force with which a mass is attracted toward the center of earth by gravity. |
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Term
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Definition
| wector quantity equal to a force (F) times the distance (d) from the point of rotation that is perpendicular to the force. M=F*d |
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Term
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Definition
scalar quantity equal to the force times distance of displacement.
W=F*s |
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Term
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Definition
| (P) Rate of doing work per unit of time |
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Term
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Definition
| Measure of a bodys capacity to do work. |
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Term
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Definition
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Term
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Definition
Ability of a body to do work because of position or state.
PE = Hieght x weight = mgh |
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Term
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Definition
Ability of a body to do work because of its motion
KE = 1/2mV2 |
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Term
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Definition
Law 1 - Equillibruim
Law 2 - Acceleration
Law 3 - Interaction
(EAI) |
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Term
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Definition
| A body at rest tends to stay at rest, a body in motion tends to stay in motion in a straight line at a constant velocity unless acted on by some unbalanced force. |
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Term
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Definition
| an unbalanced force acting on a body produces an acceleration in the direction of the force that is directly proportional to the force and inversely proportional to the mass of the body. |
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Term
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Definition
| For every action there is an equal and opposite reaction. |
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Term
| Give a flight example of Newtons 1st Law |
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Definition
| An aircraft in equillibrium flight |
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Term
| Give an example of Newtons 2nd Law |
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Definition
| Airplanes thrust causing it to move forward. |
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Term
| Give a flight example of Newtons 3rd Law |
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Definition
| Thrust produced by a jet engine. |
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Term
| Define Equillibrium flight. |
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Definition
| absence of acceleration, either linear or angular. Equilibrium exists when the sum of all forces and the sum of all moments aroudn the center of gravity equal zero |
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Term
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Definition
| Trimmed flight exists when the sum of the moments around the CG is zero. |
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Term
| Tell me about being in trimmed and equillibrium flight. |
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Definition
Equillibrium = Trimmed
Trimmed does not always = equillibrium because you can be trimmed into a turn. |
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Term
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Definition
| pressure each air particle exerts on another. Fore acts perpendicualar to any surface the air particles collide with. |
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Term
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Definition
| Total mass of air particles per unit volume. |
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Term
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Definition
| Measure of the average kinetic energy of the air particles. (T) |
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Term
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Definition
Temperature decrease with an increase in altitude.
2 degrees C
3.57 degrees F |
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Term
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Definition
| Amount of water vapor in the air. |
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Term
| As humidity increases, air density _______ |
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Definition
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Term
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Definition
| Measure of the air's resistance to flow and shearing. |
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Term
| Air Viscosity increases with an increase in _______ |
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Definition
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Term
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Definition
| Rate at which sound waves travel through a particular air mass. |
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Term
| LSOS is dependant only on ___________ |
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Definition
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Term
| As the Temperature of Air increases, the LSOS ___________ |
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Definition
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Term
| State the relationship between humidity and air density |
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Definition
| As humidity increases, air density decreases. |
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Term
| State the relationship between temperature and LSOS |
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Definition
| As Temprature increases, LSOS increases. |
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Term
| State the relationship between altitude and Temperature, Pressure, density, and LSOS |
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Definition
| Temp, pressure, density, and LSOS all decrease with an increase in altitude. |
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Term
| The 5 Major Aircraft Compenents are: |
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Definition
| Fuselage, Empenage, Landing Gear, Wings, Engine |
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Term
| What is the largest factor that increases stall speed. |
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Definition
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Term
| State the relationship between pressure, temprature, and density using the General Gas Law |
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Definition
P=pRT
While density is constant - Increasing Pressure will increase temprature.
While pressure is constant - there is an inverse relationship between density and temperature.
Increasing temp will decrease density
Increasing density will decrease temp |
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Term
| All changes in aircraft pitch occur about the? |
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Definition
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Term
| If doubled ________ causes the greatest increase in lift. |
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Definition
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Term
| What is the equivalent to ƒ |
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Definition
| A combo of an aircrafts cross sectional area presented to the relative wind and other aircraft surfaces which air flows. |
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Term
True or False
Vortices can cause one or both wings to stall on a trailing aircraft. |
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Definition
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Term
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Definition
| The ability of the prop to turn engine output into thrust. |
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Term
| Define, Compare, Contrast an aircraft and an airplane. |
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Definition
Aircraft-any device intended for use in air. balloon, glider, etc.
Airplane - Heavier than air fixed wing aircraft driven by an engine and supported by the dynamic reaction of airflow over its wings.
Aircraft describes a broad range - airplane is a more specific flying machine. |
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Term
| List and describe 3 major control surfaces. |
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Definition
Ailerons - (and spoilers) control roll
Rudder - attached to the vert stab and controls yaw
Elevator - horizontal part of empenage that controls pitch |
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Term
| List and Describe the 5 major components of an airplane |
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Definition
Fuselage - Basic Structure
Wing - Produces Lift
Empennage - Provides greatest stabilizing influence
Landing gear - ground taxi, shock absorbing
Engine - provides thrust for flight |
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Term
| List and define the components of the airplane reference system. |
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Definition
CG - point at which all weight is considered to be concentrated. All forces and moments take place around it
Longitudinal Axis - Passes from nose to tail of airplane
Lateral Axis - Wingtip to wingtip
Vertical Axis - Passes vertically through the CG |
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Term
| Describe the orientation between the components of the airplane reference system. |
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Definition
| The reference system consists of 3 mutually perpendicular axes intersecting at the CG |
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Term
| List and describe the motions that occur around the CG |
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Definition
Roll or Lateral control - movement of lateral axis around the longitudinal
Pitch - movement of the longitudinal around the lateral
Yaw or directional - Movement of longitudinal around the vertical. |
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Term
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Definition
| (b) length from wingtip to wingtip |
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Term
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Definition
| infinately long straight line drawn through the leading edge and trailing edge of an airfoil |
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Term
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Definition
| measure of the width of the wing or other control surface measured along the chordline from leading edge to trailing edge. |
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Term
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Definition
| CT - Chord Measured at the wingtip |
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Term
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Definition
| CR - Chord at wing centerline |
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Term
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Definition
| (c) average of every chord from root to tip |
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Term
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Definition
(S) apparent surface area of a wing from tip to tip
S=b*c |
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Term
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Definition
| Reduction in the chord of an airfoil from root to tip. The T34 and T-37 are tapered to reduce weight, improve structural stiffness, and reduce wingtip vortices. |
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Term
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Definition
λ = CT/CR
Ratio of tip chord to root chord |
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Term
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Definition
Angle between a line drawn 25% aft of the leading edge and the lateral axis
Λ |
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Term
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Definition
AR = b/c
Ratio that shows lift |
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Term
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Definition
WL = w/S
Ratio of weight to surface area. Tends to be an inverse relationship between AR and WL |
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Term
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Definition
| Angle between the airplane's longitudinal axis and the chordline of it's wing |
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Term
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Definition
| Angle between the spanwise inclination of the wing and the lateral axis. The T-34 and T-37 both have dihedral wings to improve lateral stability. |
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Term
| Describe the advantages of a semi-monocoque fuselage |
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Definition
| Semi monocoque aircraft have skin transverse frame members, and stringers which share stress loads and may be rapidly repaired. T-34 and T-37 have semi monocoque |
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Term
| Describe full cantilever wing construction. |
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Definition
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Term
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Definition
| Exists if at every point in the airflow static pressure, density, temprature, and velocity remain constant over time. A particle of air follows the same path as the one in front of it. |
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Term
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Definition
| The path that air particles follow in a steady airflow. |
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Term
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Definition
| A collection of streamlines forms a streamtube, which contains a flow just as effectively as a tube with solid walls. Streamtube is a closed system. Therefore total mass and energy remain constant |
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Term
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Definition
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Term
| Describe the relationship between airflow velocity and cross sectional area within a streamtube using the continuity equation. |
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Definition
| If the cross sectional area decreases on one side of the equation, velocity must increase on the same side so both sides remain equal. Velocity and area in a streamtube are inversely related. |
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Term
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Definition
PT = PS + q
Total Pressure AKA Head Pressure is = static pressure + dynamic pressure. |
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Term
| List the components of the pitot-static system |
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Definition
| Pitot tube, static pressure source, black box. |
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Term
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Definition
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Term
| Static Pressure Port Collects? |
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Definition
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Term
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Definition
| Takes static pressure and subtracts it from total pressure. The remaining static pressure is = to dynamic pressure and displayed in the cockpit. |
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Term
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Definition
| Indicated Airspeed - Indication for dynamic pressure the airplane is creating during flight. |
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Term
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Definition
| IAS corrected for instrument error. |
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Term
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Definition
| Equivalent airspeed - CAS corrected for compressibility error. EAS = TAS at sea level on a standard day. |
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Term
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Definition
| True Airspeed - actual velocity at which the airplane is moving through an air mass. |
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Term
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Definition
| Mach - Ratio of airplanes true airspeed to LSOS |
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Term
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Definition
| Critical mach number - the mach number where sonic flows will start to be experienced somewhere on the airplane. |
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Term
| Describe the effect of altitude on Mach and critical Mach number |
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Definition
| As altitude increases mach# would increase because LSOS is decreasing. |
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Term
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Definition
| Angle between an airplane's longitudinal axis and the horizon. |
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Term
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Definition
| The path described by an airplanes CG as it moves through an air mass |
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Term
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Definition
| Airflow the airplane experiences as it moves through the air. Equal in magnitude and opposite direction of FP |
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Term
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Definition
| Angle between the relative wind and the chordline of an airfoil. FP, RW, AOA should never be inferred from pitch attitude. |
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Term
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Definition
| line drawn halfway between the upper and lower surfaces |
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Term
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Definition
| If mean camber is above the chordline |
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Term
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Definition
| If the mean camber is below the chordline. |
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Term
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Definition
| If the mean camber line is coincident with the chordline. |
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Term
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Definition
| Point along the chordline where all changes in aerodynamic force take place. |
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Term
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Definition
| Height of the airfoil profile. Point of max thickness corresponds to the AC |
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Term
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Definition
| Airflow that travels along the span of the wing parallel to the leading edge. Does not produce lift. |
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Term
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Definition
| air flowing at right angles to the leading edge of an airfoil. It produces lift. |
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Term
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Definition
| aerodynamic force - force that is a result of pressure and friction distribution over an airfoil. LIFT AND DRAG |
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Term
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Definition
| Component of airodynamic force (AF) acting perpendicular to the relative wind. |
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Term
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Definition
| D - component of aerodynamic force acting parallel and in the same direction as the relative wind. |
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Term
| Describe the effects on q, static pressure, and AF as air flows around a symmetric airfoil. |
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Definition
| At zero AOA velocity increases and static pressure decreases the same on the upper and lower surfaces. Since there is no pressure differential perpendicular to the relative wind, no lift is created. |
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Term
Describe the effects on q, static pressure, and AF as air flows around a cambered airfoil.
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Definition
| Produces uneven pressure distribution at zero AOA. Because of positive camber velocity above is greater than above and pressure below is greater than above and creates lift. |
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Term
| Describe the effects of changes in AOA on the pressure distribution and AF on cambered and symetric airfoils. |
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Definition
| AOA on any airfoil causes area of the streamtube above the wing to decrease. This creates greater velocity above which in turn creates a greater pressure differential and increases AF |
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Term
| Describe changes in density |
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Definition
| Increase in density or velocity will create more lift. |
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Term
| Describe the effect of surface area |
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Definition
| More surface area will create more lift |
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Term
| Describe the effects of camber |
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Definition
| an increase in camber will produce more lift |
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Term
| Describe the effects of AOA |
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Definition
| Increase in AOA will produce greater lift. |
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Term
| List the factors affecting lift the pilot can directly control |
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Definition
| AOA, Velocity, Density, Surface area, Camber |
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Term
| Compare and contrast CL generated by cambered and symmetric airfoils. |
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Definition
Positive Camber - @ Zero AOA positive camber airfoil makes positive CL
Negative Camber - @ Zero AOA negative camber airfoil makes negative CL
Symmetric Airfoil - @ Zero AOA symmetric airfoil makes no positive or negative lift. |
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Term
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Definition
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Term
| Describe the relationship between weight, lift, velocity, and AOA IOT maintain level flight. |
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Definition
| IOT maintain level flight while increasing AOA velocity must be decreased. Otherwise the aircraft would climb. Velocity and AOA are inversely related in level flight. |
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Term
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Definition
| Layer of airflow over a surface that demonstrates local airflow retardation due to viscosity. |
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Term
| List the two types of boundary layer airflow |
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Definition
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Term
|
Definition
| monecules move smoothly along in streamlines. Produces little friction but is easily separated from surface. |
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Term
|
Definition
| Streamlines break up and flow is disorganized and irregular. Higher friction drag, adheres to upper surface better, delays boundary layer seperation. |
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Term
| State the advantage/disadvantage of laminar flow |
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Definition
Adv - little friction
DisAdv - Easily seperated from surface |
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Term
| State the advantages and disadvantages of turbulent flow. |
|
Definition
Adv - adheres to airfoil and delays boundary layer seperation.
DisAdv - High friction drag. |
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Term
| State cause and effect of boundary layer seperation. |
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Definition
-Adverse pressure gradient impedes flow of boundary layer
-If boundary layer does not have sufficient kinetic energy to overcome adverse pressure gradient the lower levels of the boundary layer will stagnate.
-The boundary layer will seperate from the surface and cause the airfoil to lose the suction pressure that causes lift. |
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Term
| Define stall and its cause and effect. |
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Definition
Stall - A condition in flight where an increase in AOA has resulted in a decrease CL
The only cause of a stall is the exsessive AOA beyond CLMAX |
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Term
| Define and state the importance of CLmax |
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Definition
| is the peak coefficient of lift and any increase of AOA beyond CLmax will decrease CL |
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Term
| Define and state the importance of CLmax AOA |
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Definition
| is known as the stalling AOA or critical AOA and the region beyond CLmaxAOA is the stall region. |
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Term
| List the methods of stall warning in the T-34 and T-37 |
|
Definition
AOA indicators
Rudder pedal shakers
stick shakers, horns, buzzers, warning lights, electronic voices. |
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Term
|
Definition
|
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Term
|
Definition
| The minimum TAS required to maintain level flight at CLmaxAOA |
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Term
| Describe the effect of weight on stall speed |
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Definition
| A reduction in weight will decrease stall speed. |
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Term
| Describe the effect of altitude on stall speed. |
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Definition
| An increase in altitude will increase stall speed. |
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Term
| Describe the effect of thrust on stall speed. |
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Definition
| Power on stalls will be less than power off stalls because at high pitch attitudes part of the weight of the airplane is being supported by the vertical component of thrust. |
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Term
| State the purpose of high lift devices |
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Definition
| Reduce takeoff and landing speeds by reducing stall speed. |
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Term
| State the effect of boundary layer devices on the coefficient of lift, stall speed, stalling AOA. |
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Definition
Coefficient of lift is increased
Stalling AOA is increased
Stall Speed is decreased. |
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Term
| What are the two types of boundary layer control devices. |
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Definition
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Term
|
Definition
| Gaps located at the leading edge of a wing that allow air to flow from below the wing to the upper surface. |
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Term
|
Definition
| movable leading edge sections that form slots |
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Term
| Describe the operation of fixed slots |
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Definition
| Leading edge air is directed through the slot, which acts like a nozzle converting static pressure into dynamic pressure. The high kinetic energy air leaving the nozzle increases the energy of the boundary layer and delays seperation. |
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Term
| When slats are deployed it opens a |
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Definition
|
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Term
| State the effect of flaps on coefficient of lift, AOA, and stall speed. |
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Definition
Coefficient of lift is increased
Stalling AOA decreases
Stall speed is decreased |
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Term
|
Definition
| Plain flaps are simple hinged flaps that increase camber |
|
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Term
|
Definition
| it is a plate deflected from the lower surface of the wing. It creates alot of drag. |
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Term
|
Definition
| similar to a plain, but moves away fromt he wing to open a narrow slot for boundary layer control. |
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Term
|
Definition
| Used extensively on larger aircraft. moves down and increases camber, and aft increasing wing area and opens a slot for boundary layer control. |
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Term
| Describe a leading edge flap |
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Definition
| Changes camber at the leading edge of the airfoil. Similar to a trailing edge plain flap. |
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Term
| State the stall pattern of a rectangular wing |
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Definition
| Strong Root stall tendancy - provides adequate stall warning and aileron effectiveness. |
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Term
| State the stall pattern of an elliptical wing. |
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Definition
| Has even lift distribution and all sections will stall at the same AOA, little warning and loss of aileron control. |
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Term
| State the stall pattern of a moderate taper wing. |
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Definition
| All sections stall at same AOA, little warning and loss of aileron effectiveness. |
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Term
| State the stall pattern of a high taper wing. |
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Definition
| Good structural stiffness but strong tip stall tendancy. |
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Term
| State the stall characteristics of a swept wing. |
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Definition
| Strong tip stall tendancy and rapidly progresses over remainder of the wing. |
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Term
| State the advantage and disadvantage of tapering the wings of a T-43C and T-37 |
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Definition
Adv - reduce weight, improve stiffness, and reduce wingtip vortices.
DisAdv - Wing stalls evenly and ailerons lose lateral control. |
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Term
| State the purpose of wing tailoring. |
|
Definition
| Create root to tip stall progression and give the pilot warning and ensure ailerons remain effective up to complete stall. |
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Term
|
Definition
| Reduction in the angle of incidence. |
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Term
|
Definition
| Reduction in camber and or thickness from root to tip. |
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Term
| State the wing tailoring on the T-34C |
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Definition
Geometrically twisted 3.1 degrees
Aerodynamically twisted to create a reduced camber at the tip. |
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Term
| State the wing tailoring on the T-37 |
|
Definition
Geometrically twisted 2.5 degrees
Aerodynamically twisted to reduce camber at the tip. |
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Term
|
Definition
Is the component of the Aerodynamic Force that is parrelell to the relative wind and acts in the same direction
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|
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Term
|
Definition
| All Drag that is not associated with the production of lift. |
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Term
|
Definition
| Is that portion of total drag associated with the production of lift. |
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|
Term
| List the three major types of parasite drag |
|
Definition
| Induced, Friction, Interference |
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Term
| State the cause of form drag |
|
Definition
| Also known as pressure or profile drag, is caused by the airflow seperation from a surface and the wake that is created by that seperation |
|
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Term
| State the cause of friction drag |
|
Definition
| Due to viscosity, a retarding force called friction drag is created in the boundary layer. |
|
|
Term
| State the cause of interference drag |
|
Definition
| Generated by mixing of streamlines between one or more components. |
|
|
Term
| State a design feature to reduce form drag |
|
Definition
|
|
Term
| State a design feature that reduces friction drag |
|
Definition
|
|
Term
| State a design feature that reduces interference drag |
|
Definition
| Proper fairing and filleting. |
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|
Term
| Equivalent parasite area is |
|
Definition
| equal to the area of a flat plate perpendicular to the relative wind that would produce the same amount of drag as form drag, friction drag, and interference drag combined. |
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