basic aerodynamics & airframe design

Variation of Ambient Temperature with Altitude

FIGURE 1/1

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

FIGURE 1/3

EAS - Altitude Curve

FIGURE 1/4

Aspect Ratio =

cbbCC

S TIPROOT .).2

( =+=Wing Area =

c

b

S

bAR ==

2

Wing Characteristics

FIGURE 1/5

Lift of Wing Sections

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 .

=

FIGURE 1/7

Wing CL - α Curve

FIGURE 1/8

Spanwise Lift Distribution

Spanwise Lift Distribution with Fuselage

Figure1/8A

FIGURE 1/9

Wing Stiffness

FIGURE 1/10

Fin Efficiency - Effect of Torsional Deflection on Incidence

Figure1/11

Fin Efficiency - Effect of Bending Deflection on Incidence

Table1/1

Table of Standard Atmospheres

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

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

Comparison of Symmetric Manoeuvre Envelopes

FIGURE 2/3

Rolling Manoeuvre Envelope

FIGURE 2/4

Gust Envelope

FIGURE 2/5

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

Wing & Fuselage Loading

FIGURE 2/7

FIGURE 2/8

Stable & Unstable Aircraft

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

Comparison of UK & US Permissible Flight Loads

Table2/2