syst 460/560 george mason university spring 2005catsr.ite.gmu.edu/introatc/aerodynamics[1].pdf ·...
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CENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCHCENTER FOR AIR TRANSPORTATION SYSTEMS RESEARCH
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Aerodynamics
SYST 460/560
George Mason UniversitySpring 2005
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Ambient & Static Pressure
Static Pressure
Ambient Pressure
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Ambient and Static Pressure• Two pressures:
• Static– Pressure on body in flow– Pressure drops due to local speed of flow
• Ambient– Pressure in neighborhood of moving body, but far enough away not to be
affected by flow
• Ambient Pressure > Static Pressure• Altitude and Airspeed measured by Static Pressure (through
static pressure port)• Correction is necessary to determine Ambient Pressure
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Ambient and Static Pressure
• Ambient pressure = δ• Pressure Altitude < 36,089 ft
δ = ( 1-6.88 X 10-6 Pressure Altitude)5.26
• Pressure Altitude > 36,089 ftδ = (0.223360 e [(36089 – Pressure Altitude)/20805.7]
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Altitude• Altitude Measurements (4):
1. Pressure Altitude– Pressure differential with respect to Pressure at Sea Level
2. Geometric Altitude– Physical distance between aircraft and reference (e.g. Sea Level)
3. Density Altitude– Difference in density with International Standard Atmosphere (ISA)
temperature4. Geopotential Altitude
– Distance between Center of Earth and parallel surfaces around the spherical earth
– Gravitational potential same on a surface
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Speeds
• Measurement of speeds on ground - easy• Ground does not move or deform
• Measurement of speeds in the air – difficult• Air moves (i.e. wind) and deforms (compresses)
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Speeds: Pitot-Static SystemStatic Pressure
Total Pressure
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Speeds: Pitot-Static System• Measures difference in air pressure between tip and
side ports• Tip = Total Pressure = pt• Side = Static Pressure = ps
• Dynamic pressure = q = pt – ps = ½ ρ V2
– ρ = density (slugs/ft3) = 0.002377– V = True Airspeed (ft/sec)
• Applies only at:– standard sea-level conditions– Speeds low enough not to air mass to compress
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Speeds
• Aircraft have high speeds and high altitude• Pitot-static system calibrated at sea-level• Distortions compensated
Indicated Airspeed
True Airspeed
Calibrated Airspeed
Equivalent Airspeed
Instrument Error
Altitude Error
Compressibility Error
Altitude Error
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Speeds
• Airspeed Measurements:1. Indicated Airspeed
– airspeed measurement from difference in pressures2. Calibrated Airspeed
– Correcting for instrument errors3. Equivalent Airspeed
– Corrected for Compressibility effects4. True Airspeed
– Actual relative speed between aircraft and airmass– Corrected for difference in density at different altitudes
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Wings
Trailing Edge
Leading Edge
Chord
Meanline
Camber
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Wings• Leading Edge
– faces oncoming flow• Trailing edge
– opposite oncoming flow• Chord
– straight line from leading edge to trailing edge• Meanline
– Line midway between upper and lower surface• Camber
– Maximum difference between meanline and chord– Symmetrical airfoil, camber = zero
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Wings
Angle of Attack = α = AlphaAngle between oncoming flow and chord
Flight Path = direction of forward flight
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Lift & Drag
• Lift Force:• upward force created by wing moving through air
• Drag Force:• rearward force resists forward movement through
air
Drag
LiftResultant Force
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Lift
• Strength of Lift determined by:1. Airspeed2. Angle of Attack3. Planform of Wing – shape of wing from above4. Wing Area5. Density of Air
• Lift increases an Angle-of-Attack increases, upto critical Angle-of-Attack (18º - 20º)
Critical A-o-A = Stall
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Lift
Effect of Angle-of-Attack• Increased Angle-of-Attack increases left (until
stall)
Angle-of-Attack
Lift Coefficient CL
Stall
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Lift
Effect of Density of Air
Low AltitudeLow Temp (Cold)Low Moisture (Dry)
High AltitudeHigh Temp (Hot)High Moisture (Humid)
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Angles of Rotation
Roll (ϕ)
Pitch (θ) =Flight Path Angle (γ) + Angle of Attack (α)
Yaw (ψ)
Exam Question: Name 3 angles of rotation
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Axes and Angles of Rotation
Pitch (θ) =Flight Path Angle (γ) + Angle of Attack (α)
θ γ
αBody Axis
Flight path Axis
Horizontal Axis
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Axes and Angles of Rotation
Roll (ϕ)
Yaw (ψ)
Front ViewTop View
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Forces on Airplane (Vertical & Longitudinal)
θ γ
αBody Axis
Flight path Axis
Horizontal Axis
Weight
Drag
Lift
γ
Thrust
Note:Lift is perpendicular to Flight Path AxisThrust is parallel to Body AxisDrag is parallel to Flight Path AxisWeight is a result of gravity, perpendicular to Horizontal Axis
Exam Question: (1) Draw the Forces acting on an airplane in the Vertical and Longitudinal axes
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Equations of Motion (Vertical & Longitudinal)
Mass * Acceleration = Σ Forces
Mass * Flight Path Acceleration (dV/dt) = Thrust(cosα) - Drag – Weight(sinγ)
• dV/dt - ft/sec• Thrust, Drag, Weight – lbs• α, γ - radians• Mass = Weight/g, g=32.2 ft/sec2
Exam Question: Given a diagram of the Forces acting on an airplane in the Vertical and Longitudinal axes, derive the equations of motion
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Equations of Motion (Vertical & Longitudinal)
M * dV/dt = T(cosα) - D – W(sinγ)
Case 1: Level Flight, Constant SpeedLevel Flight - γ = 0Constant Speed dV/dt = 0M * 0 = T(cosα) - D – 0
0 = T(cosα) – D-T(cosα) = -DT(cosα) = D
Thrust = Drag
Exam Question: (1) What is the relationship between Thrust and Drag for level flight and constant speed(2) How much thrust is required to maintain level flight at constant speed
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Equations of Motion (Vertical & Longitudinal)
M * dV/dt = T(cosα) - D – W(sinγ)
Case 2: Level Flight, Increasing Speed (Accelerating)Level Flight - γ = 0Constant Speed dV/dt > 0M * dV/dt = T(cosα) - D – 0(M * dV/dt) + D = T(cosα)
Thrust = Drag + Force Required to Accelerate Mass
Exam Question: (1) What is the relationship between Thrust and Drag for level flight while increasing speed(2) How much thrust is required to maintain level flight while increasing speed
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Equations of Motion (Vertical & Longitudinal)
M * dV/dt = T(cosα) - D – W(sinγ)
Case 3: Climbing, Constant SpeedLevel Flight - γ > 0Constant Speed dV/dt = 0M * 0 = T(cosα) - D – W(sinγ)W(sinγ) + D = T(cosα)
Thrust = Drag + Force Required to Overcome Weight (for selected Flight Path Angle)
Maximum Angle for Climb (γMax) is determined by Max Thrust, Weight and Drag
Exam Question: What parameters determine the Maximum Climb Angle (γMax). Show equation
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Equations of Motion (Vertical & Longitudinal)
Problem:Aircraft departing airport in valley must climb in excess of 4º flight path angle
to avoid terrain. Compute Flight path angle (γ) for climb with Drag = 6404 lbs, TAS = 634 ft/sec, W=100,000lbs. T=19500. Assume α = 0, no winds.
W(sinγ) + D = T(cosα);sinγ = (T(cosα) – D)/W;cosα = cos (0) = 1;sinγ = (19500(1) – 6404lbs)/100,000lbssinγ = 0.131 radiansγ = Inverse sin (0.131radians * (360º /Π)) = 7.5º
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Forces on an Airplane (Vertical and Lateral)
Roll (ϕ)
Lift
Centrifugal Force= (V2/R)*M
Weight
Notes:Un-accelerated turnR = Radius of Turn
ϕ
Exam question: (1) Draw a free-body diagram of an aircraft in the vertical/lateral axes. (2) Identify all axes. (3) Identify all forces. (4) Derive the equations of motion.
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Equations of Motion (Vertical & Lateral)
ΣForces in Vertical Axis:• L(cosϕ) = W, L = W/ cosϕ
To maintain level flight, Lift must exceed Weight
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Equations of Motion (Vertical & Lateral)
ΣForces in Lateral Axis:(V2/R)*M = -L(sinϕ)(V2/R)*W/g + L(sinϕ) = 0 (1)
ΣForces in Vertical Axis:L(cosϕ) - W= 0L = W/ (cosϕ) (2)
• Substitute equation (2) into equation (1)(V2/R)*W/g + W (sinϕ) / (cosϕ) = 0
• Replace W with mg(V2/R)*mg/g + mg (sinϕ) / (cosϕ) = 0(V2/R)*m+ mg (tanϕ) = 0
• Solve for tanϕtan ϕ = -(V2/R)*(1/g)
• Engineering convention is to flip the sign of ϕ to eliminate the negative, sotan ϕ = -(V2/R)*(1/g)
• Solve for RR = V2/(g tan ϕ)
Turn Radius is determined by Speed (V) and Roll Angle (ϕ)
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Equations of Motion (Vertical & Lateral)
Problem:Aircraft departing an airport located in a valley must
make 180º turn of no more than 4nm turn radius to avoid high terrain. Aircraft speed (V) is 140 knots CAS (= 255 fps TAS). Will 15º roll angle be enough?
R High terrain
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Equations of Motion (Vertical & Lateral)
Solution:R = V2/(g tan ϕ)R = (255ft/sec) 2/ (32.2 ft/sec) (tan (15º * Pi/360 º)R = 7548 ftConvert feet to n.m. (1nm = 6076 ft)R = 1.24 nm