Oaa - Pf - Ch1,2,3,4

Front 1

Unit of force ?

Back 1

Newton

.,~

Front 2

Weight is the result of .... .

Back 2

Force on mass
due to gravity

Front 3

Unit of work ?

Back 3

Joule
Newton - meter

[NOT watt]

Front 4

Unit of power ?

Back 4

Watt

`.,`

Front 5

Work formula

Back 5

Force (N) × Distance (m)

Front 6

Definition of power ?

Back 6

Rate of doing work

Front 7

Power formula ?
[2]

Back 7

* Work ÷ Time
in other word
* F times distance moved @ one S

Front 8

Kinetic energy is ....... .

Back 8

> The energy
> a mass possesses
> because of its motion

Front 9

Unit of Kinetic energy ?

Back 9

Joule

`.,`

Front 10

Based of Kinetic energy
a .... can apply .... by ..... .

Back 10

* moving mass
* force
* being brought to rest

Front 11

If a body's KE is increased,
a ... must have been applied.

Back 11

force

.`,.`

Front 12

KE formula

Back 12

½ m V²

Front 13

Property of inertia is said to be .... .

Back 13

> the opposition
> which a body offers
> to a change in motion

Front 14

Definition of velocity ?
Definition of acceleration ?

Back 14

Rate of change of displacement
Rate of change of velocity

Front 15

Definition of momentum

Back 15

> Quantity of motion
> possessed by a body

Front 16

Momentum formula ?

Back 16

Mass (kg) × Velocity (m/s)

Front 17

Lower layer of Atm contain the greater proportion of the whole mass because :

Back 17

air is compressible

Front 18

With increasing altitude
temperature will ...... .

Back 18

decrease continuously
UP TO 36,090 ft

Front 19

With increasing altitude
Px will .... .

Back 19

fall steadily

Front 20

With increasing altitude
Density will .... .

Back 20

decrease steadily

Front 21

@ aviation
Static Px can be measured in ...
while the SI unit for it is ... .

Back 21

* hPa
* N/m²

Front 22

Static Px is the product of ......... .

Back 22

> Mass of air
> pressing down @ air beneath

Front 23

Air density is ... .
[def]

Back 23

Mass per unit volume

Front 24

ISA was designed for ..... and ...... .

Back 24

* Px instrument calibration
* A/C perf calc. comparison

Front 25

ISA standard Atm @ SL :
T / P / D / LR

Back 25

T : 15
P : 1013.25 hPa
D : 1.225 kg/m³
LR : 1.98 / 1000ft up to 11,000m

Front 26

Object placed @ path of moving mass of air
is subjected to :
[kinds of Px]

Back 26

Dynamic AND static Px

Front 27

Dynamic Px ?
[def]

Back 27

> the AMOUNT
> by which Px rises
> @ a point where
> a moving airflow
> brought comp. to rest

Front 28

Dynamic Px equals
[formula]

Back 28

½ ρ TAS²

Front 29

Static Px vent positioning ?

Back 29

@ part of structure
> undisturbed airflow
> PARALLEL to airflow direction

Front 30

CAS is .... corrected for ... .

Back 30

IAS
positon error

Front 31

EAS is ... corrected for ... .

Back 31

* IAS
* Pos error & compressibility

Front 32

Position error is due to ....... .

Back 32

Variations in Px sensed
@ pitot / static ports

Front 33

IAS reads TAS when ?

Back 33

when amb. density
is ISA see level

Front 34

Speed of sound vs. Temp.

Back 34

* Speed of sound
> prop. to
> √ absolute air Temp.

Front 35

Mach number formula

Back 35

TAS ÷ local speed of sound

Front 36

A/C's Mcrit is ... .

Back 36

A/C's mach no.
when airflow over it
first reaches local speed of sound

Front 37

Cross sectional area of airflow
mechanically reduced :
.... remains constant
.... increases

Back 37

mass flow
velocity of airflow

Front 38

Px plus KE is constant refers to ... .

Back 38

Bernoulli's theorem

Front 39

@ streamlined airflow
closely spaced streamlines indicates ... .

Back 39

decreased Static Px
increased Velocity

Front 40

@ streamlined airflow
Converging streamlines indicates ... .

Back 40

accelerating airflow
resultant decrease in static Px

Front 41

@ streamlined airflow
Diverging streamlines indicates ... .

Back 41

decelerating airflow
resultant increase in static Px

Front 42

Streamtube is a .... to aid .... .

Back 42

* concept
* understand ing of AD force generation

Front 43

@ less than 40% speed of sound
change in ... due to ... is insignificant.

Back 43

density
dynamic Px

Front 44

Based on Principle of continuity
change in .... of a streamline flow will ..... .

Back 44

* cross-sectional area
* affect air velocity

Front 45

"Energy & mass can neither be created nor destroyed, only changed from one form to another"
refers to ... .

Back 45

Principle of continuity

Front 46

Angle of incidence is .... .

Back 46

* btw
> chord line
> & hor. datum/ long. axis of A/C

Front 47

Aerodynamic incidence / AOA is ... .

Back 47

* btw
> chord line
> & relative airflow

Front 48

Thickness chord ratio is ... .

Back 48

* max thickness of aerofoil
> as a % of the chord

Front 49

Location of Max thickness @ aerofoil is measured as ...

Back 49

a % of the chord
aft of LE

Front 50

Chord line @ aerofoil is .... .

Back 50

* a "straight line"
> joining center of curvature
> of leading & trailing edge

Front 51

Lift is the .... which acts at .... .

Back 51

* AD force
* 90 deg to "relative airflow" / flight path

Front 52

Drag acts ... to the flight path

Back 52

parallel

.,~

Front 53

AOA increase @ symmetrical aerofoil
CP will ... .

Back 53

remain unaffected

Front 54

Lift increase due to increase in speed in mainly because of ... .

Back 54

* inc of air speed passing
> over the upper AF surf.
* creating greater Px differential
> btw up & lo

Front 55

Center of Px is ... .

Back 55

* point @ AF section
> through which lift acts

Front 56

line drawn from LE to TE of AF section
equidistant @ all points from up & low surface

Back 56

mean chamber line

Front 57

@ Zero AOA
Px @ upper side of
symmetrical aerofoil is ... .
[vs. atm Px]

Back 57

less than atm Px

Front 58

Inc AOA
@ +Ve cambered aerofoil
CP movement ?

Back 58

Fwd along the chord line

Front 59

> Relative airflow
> free stream airflow
> relative wind
> a/c flight path
* all ... but .... .

Back 59

* parallel
* a/c flight path : opp in direction

Front 60

Thickness/Chord ration is expressed as ...

Back 60

% of the chord

Front 61

Airflow over rounded LE vs. sharp LE
Which one easier ?

Back 61

rounded

Front 62

Max Camber is .... .

Back 62

* Max distance
> of mean camber line
> from chord line

Front 63

@ Constant dynamic Px
Px differential may be increased by ... .

Back 63

inc AOA

?~.`,

Front 64

Aerodynamic center is located @ ....

Back 64

Approx 25% chord

Front 65

Pitching moment
around aerodynamic center

Back 65

* constant @ normal AOA

Front 66

Moment around
aerodynamic center
= .... .

Back 66

dist. AC to CP
x
lift force