me403 chapter 2 2d airfoil aerodynamics lift is mainly provided by the wing with an airfoil...
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ME403 Chapter 22D Airfoil Aerodynamics
Lift is mainly provided by the wing with an airfoil
cross-section shape
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Airfoil Geometry
An airfoil is the 2D cross-section shape of the wing, which creates sufficient lift
with minimal drag
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Historical Airfoils
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Historical Airfoils
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Typical Streamlines
Angle of Attack
chord lineV
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Pressure Distribution
99500
99550
99600
99650
99700
99750
99800
99850
99900
99950
100000
0 0.2 0.4 0.6 0.8 1
Chordwise Distance, x, m
Su
rfa
ce P
ress
ue
, P, N
/sq
m
Net Normal Force
Upper Surface Pressure
Lower Surface Pressure
n P P dxl
c
u ( )0
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Pressure Coefficient Distribution
02
2
1
V
ppcp
2
2
1
V
ppcp
In free-stream:
At stagnation point (V=0): 12
2
1
2
2
1
2
2
10
0
V
V
V
ppcp
Positive Cp means the pressure is higher than the free-stream (atmospheric) pressure, and negative Cp means suction relative to free-stream pressure. The maximum, which occurs at the stagnation point, is always 1.
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Viscous Boundary Layer
Transition Separation
1 23
4
V Edge of boundary layer
Velocity profile creates skin friction (shear) drag on surface
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Curve fit formula for turbulent boundary layer (Re > 500,000):
Flat Plate Skin Friction Drag Coefficient
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Evolution of Airfoil Design
Laminar boundary layer creates less skin
friction drag
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Boundary Layer Flow Separation
When flow separation occurs, there is also pressure drag.
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100% Pressure Drag
Pressure (Form) Drag due to Flow Separation
Total Profile Drag= Skin Friction Drag
+ Form Drag
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Resultant Aerodynamic Force
Airfoil
Total Aerodynamic Force(Sum of Pressure and Shear)
Lift
Drag
V
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Lift & Drag Coefficients
Chord Line
normal forcelift
V
drag
chordwise force
SV
lcl 2
2
1
SV
dcd 2
2
1
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Center of PressureThe resultant aerodynamic force acts at the Center of
Pressure (c.p.), about which the moment is zero.
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NACA Airfoils and Test Data
4-Digit Series
5-Digit Series
6 Series
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Open-Circuit Wind Tunnel
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Wind Tunnel Tests
Force transducer behind model senses lift, drag and pitching moment directly.Motor-controlled mechanism adjusts the model’s angle of attack.
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Closed-Circuit Wind Tunnel
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Wing Section Models
Model for measuring lift, drag and pitching moment
Model for measuring surface pressure distribution
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There is a maximum Lift-to-Drag ratio (L/D).
Location of Center of Pressure (c.p.) varies
with
NACA 0006 Dataat Re = 3,180,000
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NACA 2312 Data at Re = 3,120,000
Lift decreases and drag increases sharply beyond the stall (max. Cl) point, due to boundary layer separation.
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Stalled Airfoil
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Reynolds Number Effect
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Since the c.p. varies with , it is more desirable to use a fixed Aerodynamic Center (a.c.) as the point of action of the lift and drag. The pitching moment about this point can be calculated, and is found insensitive to . For most
airfoils, the a.c. locates at around quarter chord (x=c/4).
Aerodynamic Center
cm
V Scm
1
22
Pitching Moment Coefficient:
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Typical Non-Cambered AirfoilLift Curve & Drag Polar
NACA 0006
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Typical Cambered AirfoilNACA 2412
Lift Curve & Drag Polar
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Airfoil Aerodynamic Characteristicsat Re = 6 million
NACA 0006 NACA 2412
Zero-Lift Angle of Attack (deg.) 0 -2
Stall Angle of Attack (deg.) 9 16
Maximum Lift Coefficient 0.9 1.7
Lift Curve Slope (1/deg.) 0.1 0.108
Moment Coefficient (before stall) 0 0.05
Minimum Drag Coefficient 0.005 0.006
Max. Lift-to-Drag Ratio (L/D) 0.7/0.0076 = 92.1 1.0/0.0088 = 113
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Computation Fluid Dynamics Simulation
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CFD Simulation: Near stall
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CFD Simulation: Fully Stalled
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Airfoil Generator at http://www.ae.su.oz.au/aero/info/index.html
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Airfoil Analysis Code at http://www.ae.su.oz.au/aero/info/index.html