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![Page 1: MAE 3241: AERODYNAMICS AND FLIGHT MECHANICS Review: Bernoulli Equation and Examples Mechanical and Aerospace Engineering Department Florida Institute of.](https://reader036.fdocuments.in/reader036/viewer/2022081501/56649e895503460f94b8e8ac/html5/thumbnails/1.jpg)
MAE 3241: AERODYNAMICS ANDFLIGHT MECHANICS
Review: Bernoulli Equation and Examples
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
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LECTURE OUTLINE• Review of Euler’s Equation
– Euler’s equation for incompressible flow → Bernoulli’s Equation
• Review of Basic Aerodynamics
– How does an airfoil or wing generate lift?
– What are effects of viscosity?
– Why does an airfoil stall?
– Why are golf balls dimpled?
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WHAT DOES EULER’S EQUATION TELL US?
• Euler’s Equation (Differential Equation)
– Relates changes in momentum to changes in force (momentum equation)
– Relates a change in pressure (dp) to a chance in velocity (dV)
• Assumptions we made:
– Steady flow
– Neglected friction (inviscid flow), body forces, and external forces
• dp and dV are of opposite sign
– IF dp increases dV decreases → flow slows down
– IF dp decreases dV increases → flow speeds up
• Valid for Incompressible and Compressible flows
• Valid for Irrotational and Rotational flows
VdVdp
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INVISCID FLOW ALONG STREAMLINES
022
0
0
21
22
12
2
1
2
1
VVpp
VdVdp
VdVdpV
V
p
p
Relate p1 and V1 at point 1 to p2 and V2 at point 2Integrate Euler’s equation from point 1 to point 2 taking =constant
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BERNOULLI’S EQUATION
2
222
21
1
22
2
Vp
Vp
Vp
• If flow is irrotational p+½V2 = constant everywhere
• Remember:
– Bernoulli’s equation holds only for inviscid (frictionless) and incompressible (=constant) flows
– Relates properties between different points along a streamline or entire flow field if irrotational
– For a compressible flow Euler’s equation must be used ( is a variable)
– Both Euler’s and Bernoulli’s equations are expressions of F=ma expressed in a useful form for fluid flows and aerodynamics
Constant along a streamline
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HOW DOES AN AIRFOIL GENERATE LIFT?• Lift is mainly due to imbalance of pressure distribution over the top and bottom
surfaces of airfoil
– If pressure is lower than pressure on bottom surface, lift is generated
– Why is pressure lower on top surface?
• We can understand answer from basic physics
– Continuity
– Newton’s 2nd law
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HOW DOES AN AIRFOIL GENERATE LIFT?1. Flow velocity over the top of airfoil is faster than over bottom surface
– Streamtube A senses upper portion of airfoil as an obstruction
– Streamtube A is squashed to smaller cross-sectional area
– Mass continuity AV=constant, velocity must increase
Streamtube A is squashedmost in nose region(ahead of maximum thickness)
AB
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HOW DOES AN AIRFOIL GENERATE LIFT?2. As velocity increases pressure decreases
– Incompressible: Bernoulli’s Equation
– Compressible: Euler’s Equation
– Called Bernoulli Effect
3. With lower pressure over upper surface and higher pressure over bottom surface, airfoil feels a net force in upward direction → Lift
VdVdp
Vp
constant2
1 2
Most of lift is producedin first 20-30% of wing(just downstream of leading edge)
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EVEN A FLAT PLATE WILL GENERATE LIFT
• Curved surface of an airfoil is not necessary to produce lift
– But it significantly helps to reduce drag
A
B
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EXAMPLE 2: WIND TUNNELS
• A wind tunnel is a ground-based experimental facility used to produce air flow to study flight of airplanes, missiles, space vehicles, etc.
• Many different types of wind tunnels– Subsonic, transonic, supersonic, hypersonic
Excellent Wind Tunnel Site: http://vonkarman.stanford.edu/tsd/pbstuff/tunnel/
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OPEN VS. CLOSED CIRCUIT WIND TUNNELS
Excellent Wind Tunnel Site: http://vonkarman.stanford.edu/tsd/pbstuff/tunnel/
Open-Circuit Tunnel
Closed-Circuit Tunnel
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EXAMPLE: LOW-SPEED, SUB-SONIC WIND TUNNEL
• Subsonic wind tunnels generally operate at speeds < 300 MPH
Contraction(Nozzle)
Fan
Test Section
Diffuser1
2
Why build all of this?
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EXAMPLE: LOW-SPEED, SUB-SONIC WIND TUNNEL
222
211
12
12
222111
2
1
2
1VpVp
VA
AV
AVAV
2
1
2
212
2121
22
1
2
2
AA
ppV
VppV
• At speeds M < 0.3 ( or ~ 100 m/s) flow regarded as incompressible
• Analyze using conservation of mass (continuity) and Bernoulii’s Equation
1
2
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EXAMPLE 3: MEASUREMENT OF AIRSPEED• How do we measure an airplanes speed in flight?
• Pitot tubes are used on aircraft as speedometers (point measurement)
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STATIC VS. TOTAL PRESSURE• In aerodynamics, 2 types of pressure: Static and Total (Stagnation)
• Static Pressure, p
– Due to random motion of gas molecules
– Pressure we would feel if moving along with the flow
– Pressure in Bernoulli’s equation is static pressure
• Total (Stagnation) Pressure, p0 or pt
– Property associated with flow motion
– Total pressure at a given point in flow is the pressure that would exist if flow were slowed down isentropically to zero velocity
• p0 > p
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MEASUREMENT OF AIRSPEED: INCOMPRESSIBLE FLOW
02
12
1pVp
ppV
0
1
2
Staticpressure
Dynamicpressure
Totalpressure
Incompressible Flow
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SKETCH OF A PITOT TUBE (4.11)
• Measures total pressure
• Open at A, closed at B
• Gas stagnated (not moving) anywhere in tube
• Gas particle moving along streamline C will be isentropically brought to rest at point A, giving total pressure
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EXAMPLE: MEASUREMENT OF AIRSPEED (4.11)• Point A: Static Pressure, p
– Surface is parallel to flow, so only random motion of gas is measured
• Point B: Total Pressure, p0
– Aligned parallel to flow, so particles are isentropically decelerated to zero velocity
• A combination of p0 and p allows us to measure V1 at a given point
• Instrument is called a Pitot-static probe
p0
p
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MEASUREMENT OF AIRSPEED: INCOMPRESSIBLE FLOW
02
12
1pVp
02
12
1pVp
ppV
0
1
2
Staticpressure
Dynamicpressure
Totalpressure
Incompressible Flow
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TRUE VS. EQUIVALENT AIRSPEED• What is value of ?
• If is measured in actual air around the airplane
• Measurement is difficult to do
• Practically easier to use value at standard seal-level conditions, s
• This gives an expression called the equivalent airspeed
ppVtrue
02
s
e
ppV
02
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MEASUREMENT OF AIRSPEED:SUBSONIC COMRESSIBLE FLOW
• If M > 0.3, flow is compressible (density changes are important)
• Need to introduce energy equation and isentropic relations
21
1
0
1
21
1
0
02
11
2
11
21
2
1
MT
T
Tc
V
T
T
TcVTc
p
pp
11
21
1
0
12
11
0
2
11
2
11
M
Mp
p
cp: specific heat at constant pressureM1=V1/a1
air=1.4
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MEASUREMENT OF AIRSPEED:SUBSONIC COMRESSIBLE FLOW
• So, how do we use these results to measure airspeed
111
2
111
2
11
2
11
2
1
102
2
1
1
10212
1
1
1
0212
1
1
1
021
s
scal p
ppaV
p
ppaV
p
paV
p
pM
p0 and p1 giveFlight Mach numberMach meter
M1=V1/a1
Actual Flight Speed
Actual Flight Speedusing pressure difference
What is T1 and a1?Again use sea-level conditions Ts, as, ps (a1=340.3 m/s)
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REAL EFFECTS: VISCOSITY ()• To understand drag and actual airfoil/wing behavior we need an understanding of
viscous flows (all real flows have friction)
• Inviscid (frictionless) flow around a body will result in zero drag!
– Called d’Alembert’s paradox (Must include friction in theory)
We will derive this streamlinepattern in class next week
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REAL EFFECTS: VISCOSITY ()• Flow adheres to surface because of friction between gas and solid boundary
– At surface flow velocity is zero, called ‘No-Slip Condition’
– Thin region of retarded flow in vicinity of surface, called a ‘Boundary Layer’
• At outer edge of B.L., V∞
• At solid boundary, V=0
“The presence of friction in the flow causes a shear stress at the surface of a body, which, in turn contributes to the aerodynamic drag of the body: skin friction drag”
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THE REYNOLDS NUMBER• One of most important dimensionless numbers in fluid mechanics/ aerodynamics
• Reynolds number is ratio of two forces
– Inertial Forces
– Viscous Forces
– c is length scale (chord)
• Reynolds number tells you when viscous forces are important and when viscosity can be neglected
cVRe
Within B.L. flowhighly viscous(low Re)
Outside B.L. flowInviscid (high Re)
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LAMINAR VERSUS TURBULENT FLOW• Reynolds number also tells you about two types of viscous flows
– Laminar: streamlines are smooth and regular and a fluid element moves smoothly along a streamline
– Turbulent: streamlines break up and fluid elements move in a random, irregular, and chaotic fashion
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LAMINAR VERSUS TURBULENT FLOW
All B.L.’s transition from laminar to turbulent
cf,turb > cf,lam
Turbulent velocityprofiles are ‘fuller’
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WHY DOES AN AIRFOIL STALL?• Key to understanding: Friction causes flow separation within boundary layer• Separation then creates another form of drag called pressure drag due to separation
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WHY DOES AN AIRFOIL STALL?• Key to understanding
– Friction causes flow separation within boundary layer
– Separation then creates another form of drag called pressure drag due to separation
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WHY DOES BOUNDARY LAYER SEPARATE?• Adverse pressure gradient interacting with velocity profile through B.L.
• High speed flow near upper edge of B.L. has enough speed to keep moving through adverse pressure gradient
• Lower speed fluid (which has been retarded by friction) is exposed to same adverse pressure gradient is stopped and direction of flow can be reversed
• This reversal of flow direction causes flow to separate
– Turbulent B.L. more resistance to flow separation than laminar B.L. because of fuller velocity profile
– To help prevent flow separation we desire a turbulent B.L.
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WHY DOES AN AIRFOIL STALL?• Two major consequences of separated flow over airfoil
– Dramatic loss of lift (stalling)• Separated flow causes higher pressure on upper surface of airfoil
– Major increase in drag• Separation causes lower pressure on trailing edge• Unbalance of pressure force causes pressure drag due to separation
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SUMMARY OF VISCOUS EFFECTS ON DRAG• Friction has two effects:
– Skin friction due to shear stress at wall
– Pressure drag due to flow separation
pressurefriction DDD
Total drag due toviscous effectsCalled Profile Drag
Drag due toskin friction
Drag due toseparation= +
Less for laminarMore for turbulent
More for laminarLess for turbulent
So how do you design?Depends on case by case basis, no definitive answer!
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COMPARISON OF DRAG FORCES
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GOLF BALL AERODYNAMICS
• Why are modern golf balls dimpled?
• How important is skin friction?
• How important is pressure drag (separation)?
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GOLF BALL AERODYNAMICS
Large Wake of Separated Flow, High Pressure DragLaminar B.L. Separation Point
Reduced Size Wake of Separated Flow, Lower Pressure DragTurbulent B.L. Separation Point
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GOLF BALL AERODYNAMICS
Large Wake of Separated Flow, High Pressure DragLaminar B.L. Separation Point
Reduced Size Wake of Separated Flow, Lower Pressure DragTurbulent B.L. Separation Point
Drag due to viscousboundary layer skin friction
DR
AG
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GOLF BALL AERODYNAMICS
Large Wake of Separated Flow, High Pressure DragLaminar B.L. Separation Point
Reduced Size Wake of Separated Flow, Lower Pressure DragTurbulent B.L. Separation Point
Pressure drag (due to viscousflow separation, wake)
DR
AG
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GOLF BALL AERODYNAMICS
Large Wake of Separated Flow, High Pressure DragLaminar B.L. Separation Point
Reduced Size Wake of Separated Flow, Lower Pressure DragTurbulent B.L. Separation Point
DR
AG
Total Drag
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GOLF BALL AERODYNAMICS: SUMMARY
• Pressure drag dominates spheres and cylinders
• Dimples encourage formation of turbulent B.L.
• Turbulent B.L. less susceptible to separation
• Delayed separation → Less total drag
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COMPARISON OF DRAG FORCES
d
d
Same total drag as airfoil