B1/B2 MODULE-8 AERODYNAMICS
Physics of The Atmosphere
The earth atmosphere contains: 78% Nitrogen, 21% Oxygen and 1% other gases
In still air, the pressure: Pressure exert in all direction
The aircraft operator with in the: Tropopasue
On average, Lowest part of the Troposphere is warmest:
The troposphere contains 80% mass of the atmosphere.
The Maximum mass of the atmosphere lies in Troposphere (80% of mass)
The coldest place in earth atmosphere. Poles
The Tropause is the Boundary between: Troposhpere and strasphere
The stratopause is the boundary between: Stratosphere and Mesosphere
The atmosphere layer which extends from Stratopause is: Mesosphere
Temperature laps rate take place up to an approximate height of: 36090ft, 11000m,
The standard sea level absolute temperature is: 15.15C, 278K, 59F
An adiabatic temperature change means: Temperature Change due to pressure.
Humid air will be less dense than dry air.
The atmospheric pressure at any place is equal to the weight of the column of air above it
“Naca” Stand for: National Advisory Committee for Aeronautics.
Standard atmosphere pressure at 59°F, 15C, 278K is approximately:
29.92 in Hg
1013.2 mbar
14.7 PSI
101.04 K Pa
760 mmHg
At any given altitude, the air density: air density will decrease with decrease in
atmospheric pressure as altitude increases.
The performance of A/C itself and its engine are directly affected by the change in
altitude pressure ratio.
If the properties at all point of air flow are the same the airflow is then known as a
Uniform flow.
At the tropopause the pressure decreases to about a quarter of its sea level.
On damps days the density of air is less than it is on dry days.
Altitude pressure ratio is:
𝐴𝑚𝑏𝑖𝑒𝑛𝑡 𝑝𝑟𝑒𝑠𝑠𝑢𝑟𝑒
∑= 𝑆𝑡𝑎𝑛𝑑𝑎𝑟𝑑 𝑠𝑡𝑎𝑡𝑖𝑐 𝑝𝑟𝑒𝑠𝑠𝑢𝑟𝑒
Prepared By: Syed Umair Amer “Anyone who stops learning is old, whether at twenty or eighty.
Anyone who keeps learning stays young. – Henry Ford
, B1/B2 MODULE-8 AERODYNAMICS
Aerodynamics 8.2
The curvature of an aerofoil section from the L.E to T.E is: Mean chamber line
The perpendicular distance between the chord line and the mean chamber line is:
Chamber
The angle that the chord line of an erofoil section makes with the longitudinal axis of the
aircraft is: Angel of incidene (AoI)
The forces that support an aircraft in flight can be explained principally by: L,W,D,T
As the angle of attack of an aerofoil increases, the centre of pressure: Moves forward
Boundary layer is: Varies from zero air velocity on the surface of the aerofoil to the
velocity of free stream.
Finess ratio ( C/T)
Induced drag increase with Angle of attack.
When does the angle of incidence changes: remains constant
An aspect ratio of 8:1 would mean: Span/chord (8/1).
The amount of lift generated by the wing is:
Reynolds Number ( Size, density, viscosity and speed).
The optimum angle of attack of an aerofoil is the angle at which: lift is proportional till
critical angle.
As the air flow towards an aerofoil it will be turned towards the low pressure at upper
surface this is termed as up wash
Tip spillage means that an aircraft wing never produce same amount of lift as an infinite
wing.
The aerodynamic center is defined as the point along the chord where all changes in lift
take place.
Mean aerodynamics center is the average chord length of a tapered swept wing.
Minimum total drag of an aircraft occurs: Profile drag = Induce drag
As the angle of attack increases, the stagnation point: moves downwards
As the air flows over the upper chambered surface of an aerofoil, what happens to the
velocity: Velocity increases and pressure decrease
When an aircraft stalls: after critical angle
Which of the following forces act on aircraft in level flight: (L,W,T,D)
Bernoullis Principal = Static pressure + Dynamic Pressure
The lift produced by aerofoil is then perpendicular to the relative wind
Air foil over the upper surface of the wing generally: High velocity and low Pressure
A wing section suitable for high speed would be: thin
Airflow at subsonic speed is taken to be: incompressible
To produce lift, an aerofoil must be: cambered
The difference between the mean camber line and the chord line of an aerofoil is: camber
The ratio between the chord and the maximum thickness of an aerofoil is: Finess ratio
(C/max.thickness)
The co-efficient of lift (CL) is a function of:
The parasite drag: is the function of velocity (Profile drag)
Induced drag: Is the function of AoA (Angle of attack)
Minimum drag speed is the point, where: Profile drag = Induce drag
The tip to tip distance of a wing is: span
Prepared By: Syed Umair Amer “Anyone who stops learning is old, whether at twenty or eighty.
Anyone who keeps learning stays young. – Henry Ford
Physics of The Atmosphere
The earth atmosphere contains: 78% Nitrogen, 21% Oxygen and 1% other gases
In still air, the pressure: Pressure exert in all direction
The aircraft operator with in the: Tropopasue
On average, Lowest part of the Troposphere is warmest:
The troposphere contains 80% mass of the atmosphere.
The Maximum mass of the atmosphere lies in Troposphere (80% of mass)
The coldest place in earth atmosphere. Poles
The Tropause is the Boundary between: Troposhpere and strasphere
The stratopause is the boundary between: Stratosphere and Mesosphere
The atmosphere layer which extends from Stratopause is: Mesosphere
Temperature laps rate take place up to an approximate height of: 36090ft, 11000m,
The standard sea level absolute temperature is: 15.15C, 278K, 59F
An adiabatic temperature change means: Temperature Change due to pressure.
Humid air will be less dense than dry air.
The atmospheric pressure at any place is equal to the weight of the column of air above it
“Naca” Stand for: National Advisory Committee for Aeronautics.
Standard atmosphere pressure at 59°F, 15C, 278K is approximately:
29.92 in Hg
1013.2 mbar
14.7 PSI
101.04 K Pa
760 mmHg
At any given altitude, the air density: air density will decrease with decrease in
atmospheric pressure as altitude increases.
The performance of A/C itself and its engine are directly affected by the change in
altitude pressure ratio.
If the properties at all point of air flow are the same the airflow is then known as a
Uniform flow.
At the tropopause the pressure decreases to about a quarter of its sea level.
On damps days the density of air is less than it is on dry days.
Altitude pressure ratio is:
𝐴𝑚𝑏𝑖𝑒𝑛𝑡 𝑝𝑟𝑒𝑠𝑠𝑢𝑟𝑒
∑= 𝑆𝑡𝑎𝑛𝑑𝑎𝑟𝑑 𝑠𝑡𝑎𝑡𝑖𝑐 𝑝𝑟𝑒𝑠𝑠𝑢𝑟𝑒
Prepared By: Syed Umair Amer “Anyone who stops learning is old, whether at twenty or eighty.
Anyone who keeps learning stays young. – Henry Ford
, B1/B2 MODULE-8 AERODYNAMICS
Aerodynamics 8.2
The curvature of an aerofoil section from the L.E to T.E is: Mean chamber line
The perpendicular distance between the chord line and the mean chamber line is:
Chamber
The angle that the chord line of an erofoil section makes with the longitudinal axis of the
aircraft is: Angel of incidene (AoI)
The forces that support an aircraft in flight can be explained principally by: L,W,D,T
As the angle of attack of an aerofoil increases, the centre of pressure: Moves forward
Boundary layer is: Varies from zero air velocity on the surface of the aerofoil to the
velocity of free stream.
Finess ratio ( C/T)
Induced drag increase with Angle of attack.
When does the angle of incidence changes: remains constant
An aspect ratio of 8:1 would mean: Span/chord (8/1).
The amount of lift generated by the wing is:
Reynolds Number ( Size, density, viscosity and speed).
The optimum angle of attack of an aerofoil is the angle at which: lift is proportional till
critical angle.
As the air flow towards an aerofoil it will be turned towards the low pressure at upper
surface this is termed as up wash
Tip spillage means that an aircraft wing never produce same amount of lift as an infinite
wing.
The aerodynamic center is defined as the point along the chord where all changes in lift
take place.
Mean aerodynamics center is the average chord length of a tapered swept wing.
Minimum total drag of an aircraft occurs: Profile drag = Induce drag
As the angle of attack increases, the stagnation point: moves downwards
As the air flows over the upper chambered surface of an aerofoil, what happens to the
velocity: Velocity increases and pressure decrease
When an aircraft stalls: after critical angle
Which of the following forces act on aircraft in level flight: (L,W,T,D)
Bernoullis Principal = Static pressure + Dynamic Pressure
The lift produced by aerofoil is then perpendicular to the relative wind
Air foil over the upper surface of the wing generally: High velocity and low Pressure
A wing section suitable for high speed would be: thin
Airflow at subsonic speed is taken to be: incompressible
To produce lift, an aerofoil must be: cambered
The difference between the mean camber line and the chord line of an aerofoil is: camber
The ratio between the chord and the maximum thickness of an aerofoil is: Finess ratio
(C/max.thickness)
The co-efficient of lift (CL) is a function of:
The parasite drag: is the function of velocity (Profile drag)
Induced drag: Is the function of AoA (Angle of attack)
Minimum drag speed is the point, where: Profile drag = Induce drag
The tip to tip distance of a wing is: span
Prepared By: Syed Umair Amer “Anyone who stops learning is old, whether at twenty or eighty.
Anyone who keeps learning stays young. – Henry Ford
