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Define: Scalar Quantity, Vector Quantity Force, Mass Volume, Density Weight, Moment Power, Energy 1 Potential Energy Kinetic Entergy 2 Scalar Quantity: quantity that represents only magnitude ie time or temp Vector Quantity: quantity that represents magnitude and distance ie F, a Force: m * a, it is a push pull exerted on a body Mass: m, the quantity of molecular material that compromises an object Volume: v, the amount of space occupied by an object Density: , mass per unit volume 3 Weight: the force with which a mass is attracted to the earth’s center Moment: a vector quantity equal to a force times a distance from the point of rotation that is perpendicular to the force Power: rate of doing work or work done per unit time (scalar quantity) Energy: scalar measure of a body’s capacity to do work Potential Energy: PE=mgh, ability to do work because of its position or state of being 4 Kinetic Entergy: KE=1/2mV2 5 6 State Newton’s Three Laws of Motion 7 1) Law of Equilibrium- A body at rest tends to stay at rest and a body in motion tends to remain in motion in a straight line at a constant velocity unless acted upon by some unbalanced force 2) Law of Acceleration: An unbalanced force acting on a body produces an acceleration in 8 the direction of the force that is directly proportional to the force and inversely proportional to the mass of the body 3) The Law of Interaction: For every action, there is an equal and opposite reaction 9 10 Examples of the Law’s of Motion 11 12 1) an airplane in equilibrium flight with no change in acceleration that is level and in constant velocity 2) increasing the throttle on a plane produces more thrust than drag causing 13 the airplane to accelerate till they are equal 3) if a jet fires hot gases rearward, it will move forward 14 Define, Compare and Contrast Equilibrium and Trimmed Flight 15 Equilibrium is the absence of acceleration either linear r angular. It exist when the sum of all the forces and the sum of the moment around the COG are equal to zero 16 Trimmed exist when the sum of the moments around the COG is zero. In trimmed flight, the sum of the forces may not be equal to zero since you can trim a airplane into a turn. 17 Define: Static Pressure, Air Density Temperature, Lapse Rate Humidity, Viscosity Local Speed of Sound 18 Include any important relationships 19 Static Pressure: pressure each air particle exerts on another. Atmospheric static pressure decreases with altitude increase Air Density: , the total mass of air particle per unit of volume. Air Density decreases with altitude increase Temperature: the average kinetic energy of the air particles. Lapse Rate: the linear decrease in air temperature as you increase altitude at 2oC/1000’ or 3.57oF/1000’. Decreases till 36,000’ 20 Humidity: the amount of water vapor in the air. As humidity increases, air density decreases Viscosity: a measure of the air’s resistance to flow or shearing (stickiness). Air viscosity increases with an increase in temperature Local Speed of Sound: the rate at which sound waves travel through an air mass. As temperature increases, LSOS increases. Sound is a wave motion... not particle! 21 State the pressure, temperature, lapse rate At sea level using Metric and English units for 22 A standard atmosphere 23 Metric Pressure Temperature 24 1013.2mb 15C English 29.92 in-HG 59F Lapse Rate 3.57F/1000’ 25 2C/1000’ State the relationship between altitude and temperature, 26 Pressure, air density and local speed of sound Within the standard atmosphere 27 As you increase altitude, temperature decreases to 36,000’ , pressure 28 decreases, air density decreases, and the local speed of sound decreases 29 State the relationship between Pressure, Temperature, and Air Density Using the General Gas Law 30 P=RT 31 If pressure is held constant ie constant altitude, then and temperature will be inversely proportional to eachother Bonus Card: 32 Altitude is defined as the height above a given plane of reference. True Altitude is the actual height above mean sea level Pressure Altitude is the height above the standard data plane Density Altitude is the altitude in the standard atmosphere where the air density is equal to the local air density and if found by correcting pressure altitude for temperature deviations from standard atmosphere. 33 A high DA indicates a low air density and will decrease aircraft’s performance because the power being produced by the engines is getting fewer molecules to burn 34 Define, Compare Contrast an Aircraft and an Airplane 35 An aircraft is any device used or intended to be used for flight in the air. It is either supported by buoyancy of the structure or by dynamic reaction of the air against its surfaces An airplane is a heavier than air, fixed wing aircraft that is driven by an engine (propeller or 36 jet) and is supported by the dynamic reaction of the air against its wings. 37 T-34: Unpressurized, low winged monoplane, tricycle landing gear, single engine turboprop, tandem cockpit, semi-monocoque fuselage, slotted flaps, 33’5” wingspan, tapered wings, dihedral wings, 38 List and Describe the Three major control surfaces of an Airplane 39 Ailerons – are attached to the wing to control roll Elevators – are the horizontal surface attached to the horizontal stabilizer to control pitch Rudder – is the upright surface attached to the vertical stabilizer to control yaw 40 List and describe the five major Components of an airplane 41 42 Fuselage: basic structure of the airplane to which all the other components are attached Empennage: assembly of stabilizing and control surfaces on the tail of an airplane Wing: airfoil attached to the fuselage and is designed to produce lift 43 Landing Gear: permits ground taxi and absorbs the landings shock Engine: provide the thrust necessary for powered flight 44 List and define the components of an airplane referencing system 45 Consist of three mutually perpendicular lines intersection at a point called the center of gravity. This point is where all the weight is concentrated and where all the forces and moments are measured Longitudinal Axis: passes from nose to tail, movement of the lateral around this is called roll and controlled by the ailerons 46 Lateral Axis: passes from wingtip to wingtip, movement of longitudinal axis around this axis is called pitch and controlled by the elevators Vertical Axis: passes vertically thru the COG, movement of the longitudinal axis about the vertical axis is directional control and produces yaw from the rudders 47 Define: Wingspan, Chordline, Chord Tip/Root Chord, Average Chord Wing Area, Taper, Taper Ratio, Sweep Angle 48 Aspect Ratio, Wing Loading Angle of Incidence, Dihedral Angle 49 Wingspan: b, the length of the wing from tip to tip Chordline: an infinitely long line from the leading to the trailing edges of an airfoil Chord: a measure of the width of the wing or control surface Tip/Root Chord: measure of the chord at wing tip and wing root Average Chord: c, is the average of every chord from wing root to wing tip Wing Area: S=b*c, the apparent surface area of a wing from wingtip to wingtip Taper: the reduction in the chord of an airfoil from root to tip 50 Taper Ratio: =Chord tip/root, ratio of tip chord to root chord Sweep Angle: , is the angle between a line drawn 25% aft of the leading edge and parralle to the lateral axis Aspect Ratio: AR=b/c, the ratio of the wingspan to the average chord Wing Loading: WL=weight/wing area, ratio of the planes weight to the surface area Angle of Incidence: angle between the plane’s longitudinal axis and the chordline Dihedral Angle the angel between the spanwise inclination of the wing and the lateral axis 51 52 State the advantages of 53 Semi-monocoque fuselage construction 54 Semi-monocoque fuselages have skin, transverse frame members, and stringers which all share in the stress load and are easily 55 repaired if damaged. It is the happy medium between a truss and a full-monocoque. 56 Describe a Full Cantilever Wing Construction 57 A wing with all internal bracing 58 Define: Steady Airflow, Streamlines, and Streamtube 59 60 Steady Airflow: exist if at every point in the airflow there is a steady static pressure, density, temperature and velocity Streamlines: the path that air particles follow in steady airflow 61 Streamtube: a collection of streamlines form a tube which contains flow that is effectively equivalent to a tube 62 Describe the relationship between airflow velocity 63 and cross sectional area within a stream tube using the continuity equation 64 A1V1 = A2V2 If under supersonic airflow, density is eliminated. The massflow in must equal the massflow out. If 65 A2 decreases, then V2 must increase. This makes area and velocity inversely related. 66 Describe the relationship between total pressure, static pressure, and dynamic pressure using Bernoulli’s Equation 67 Total Pressure = Static Pressure + Dynamic Pressure Total Pressure must remain constant within a closed system. As area in a streamline 68 decreases, velocity increases, dynamic pressure increases and forces static pressure to decrease. 69 List the components of a Pitot-Static System 70 Pitot Tube, Black Box, Static Pressure Port This device collects Total Pressure (Pitot Tube), and ambient Static Pressure (Static Pressure Port) 71 Q=Pt-Ps (Black Box converts Q into a IAS velocity) 72 Define: Indicate Air Speed, Calibrated AS Equivalent AS, True AS Ground Speed 73 Indicate Air Speed: instrument indication for the dynamic pressure the airplane creates during flight Calibrated AS: taking the IAS and calibrating for instrumental error (caused by the static pressure port accumulating erroneous static pressure from slip stream flow) Equivalent AS: takes the CAS and corrects for compressibility caused by the ram effect of air at high speeds. It is the true AS at sea level on a standard day that produces the same q as the actual flight conditions 74 True AS: the actual velocity at which the plane moves thru an airmass found by correcting EAS for density. TAS will equal IAS only under standard day and sea level conditions! Ground Speed: is a measure of the planes actual speed over the ground. TAS is thru an airmass and GS is corrected for wind 75 Describe the relationship of IAS, TAS, GS and Altitude 76 Air density decreases when you increase temperature and altitude, if IAS remains constant while climbing from sea level to some higher altitude, TAS must increase. TAS will be about 3 77 knots faster than IAS for every thousand feet of altitude. 78 Describe the effects of wind on IAS, TAS, and GS 79 GS is found by correcting the TAS for the movement of the air mass. GS = TAS – Headwind or + a Tailwind 80 Define: 81 Mach Number: M = TAS / LSOS, it is the ratio of the airplane’s TAS to the local speed of sound 82 Critical Mach Number: the free air stream mach number that produces the first evidence of local sonic flow 83 Define Pitch Attitude, Flight Path, Relative Wind, Angle of Attack, Mean Camber Line, Positive Camber Line, Negative Camber Line, Symmetric Camber Line, 84 Aerodynamic Center, Airfoil Thickness, Spanwise Flow, Chordwise Flow Pitch Attitude: , angle between a plane’s longitudinal axis and the horizon Flight Path: the path described by a plane’s COG as it moves thru an airmass 85 Relative Wind: the airflow the plane experiences as it moves thru the air. It is equal in magnitude and opposite in direction of the flight path Angle of Attack: , angle between the relative wind and the chorline of the airfoil Mean Camber Line: line drawn halfway between the upper and lower surfaces of a wing Positive/Negative/Symmetric Camber Line: description of the above line 86 Aerodynamic Center: is the quarter chord point of the chordline and remains constant until supersonic flight is reached (23 – 27%) Airfoil Thickness: The point of maximum thickness corresponding to the aerodynamic center Spanwise Flow: Air flow that travels along the span of the wing and produces no lift Chordwise Flow: Air flow that travels at rigth angles to the leading edge and accelerates over the wing causing lift! 87 88 Define: Aerodynamic Force, Lift 89 Drag 90 Aerodynamic Force: is a force that is the result of pressure and friction distribution over an airfoil and can be described by lift and drag Lift: the component of the aerodynamic force acting perpendicular to the relative wind 91 Drag: the component of the aerodynamic force acting parallel to and in the same direction as the relative wind 92 Describe the effects on dynamic pressure, static pressure, and the aerodynamic force as air flows around a cambered airfoil and symmetric airfoil 93 As air flows over the top of a wing, it must travel farther and at a higher velocity. The static pressure above the wing is less than the 94 pressure below creating in upward pull and a lifting force. 95 96 Describe the effects of density, velocity, surface area, camber, and angle of attack on lift 97 An increase in density or velocity or a wing’s surface area produces greater lift 98 99