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Basic Aerodynamics & Airframe Design

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Basic Aerodynamics & Airframe Design

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Page 1: Basic Aerodynamics & Airframe Design
Page 2: Basic Aerodynamics & Airframe Design
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Variation of Ambient Temperature with Altitude

FIGURE 1/1

Page 9: Basic Aerodynamics & Airframe Design

FIGURE 1/2

Measurement of Air-speed

Air-speed indicator (ASI) will read :-

Pressure in Open Tube minus Pressure in Closed Tube

i.e. ( p + ½ ρ v2 ) - (p) = ½ ρ v2

Page 10: Basic Aerodynamics & Airframe Design

FIGURE 1/3

EAS - Altitude Curve

Page 11: Basic Aerodynamics & Airframe Design

FIGURE 1/4

Aspect Ratio =

cbbCC

S TIPROOT .).2

( =+=Wing Area =

c

b

S

bAR ==

2

Wing Characteristics

Page 12: Basic Aerodynamics & Airframe Design

FIGURE 1/5

Lift of Wing Sections

Page 13: Basic Aerodynamics & Airframe Design

FIGURE 1/6

Wing Section CL, CD, CM

Lift Coefficient = Drag Coefficient =

Normal Force Coefficient

Chordwise Force Coefficient

Pitching Moment Coefficient =

Sq

LCL .

=Sq

DCD .

=

Sq

NCN .

==Sq

CCC .

==

Scq

MCM .

=

Page 14: Basic Aerodynamics & Airframe Design

FIGURE 1/7

Wing CL - α Curve

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FIGURE 1/8

Spanwise Lift Distribution

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Spanwise Lift Distribution with Fuselage

Figure1/8A

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FIGURE 1/9

Wing Stiffness

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FIGURE 1/10

Fin Efficiency - Effect of Torsional Deflection on Incidence

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Figure1/11

Fin Efficiency - Effect of Bending Deflection on Incidence

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Table1/1

Table of Standard Atmospheres

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DEF-STAN 00-970 Symmetric Flight Envelope

VH = Maximum speed in level flightVD = Design diving speed (EAS)MD = Design diving speed (Mach)n1 = Maximum normal acceleration coefficient FIGURE

2/1

Page 35: Basic Aerodynamics & Airframe Design

Tornado & EFA Symmetric Flight Envelope

VH = Maximum speed in level flightVD = Design diving speed (EAS)MD = Design diving speed (Mach)n1 = Maximum normal acceleration coefficient

FIGURE 2/2

Page 36: Basic Aerodynamics & Airframe Design

Comparison of Symmetric Manoeuvre Envelopes

FIGURE 2/3

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Rolling Manoeuvre Envelope

FIGURE 2/4

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Gust Envelope

FIGURE 2/5

Page 39: Basic Aerodynamics & Airframe Design

FIGURE 2/6

Aircraft Balance (Stable Aircraft)

L Wing & fuselage liftP Tail loadn Load factorW WeightT Engine thrustD Dragf Forward inertia factor

0.... =−−+ TlPbDcTaL

0sin. =+−− βTPnWL

Page 40: Basic Aerodynamics & Airframe Design

Wing & Fuselage Loading

FIGURE 2/7

Page 41: Basic Aerodynamics & Airframe Design

FIGURE 2/8

Stable & Unstable Aircraft

Page 42: Basic Aerodynamics & Airframe Design

Proof / Ultimate Ratio for Various Projects

Ultimate Factor Proof Factor Limit / Ultimate Proof / Ultimate Aircraft

1.5 1.125 0.67 0.75 Jet Provost, Canberra

1.5 1.0 0.67 0.67 Tornado, EAP

1.4 1.125 0.71 0.80 Not Used

1.4 1.0 0.71 0.71 EF2000

1.25 1.15 0.80 0.92

1.25 1.0 0.80 0.80

U.S unmanned a/c Proof factor not known

TABLE 2/1

Page 43: Basic Aerodynamics & Airframe Design

Comparison of UK & US Permissible Flight Loads

Table2/2