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Module 8 Basic Aerodynamics || Important Questions Fully Explained With Theory #aviation2304
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Module 8 Basic Aerodynamics || Important Questions Fully Explained With Theory #aviation2304
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Hello friends in this video we will discuss moduke 8 important questions with full theory.
if you like this video and want another video of more questions then like the video and comment below. Thank You.
An airfoil or aerofoil is the cross-sectional shape of a wing, blade (of a propeller, rotor, or turbine), or sail (as seen in cross-section).
An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag. Subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.
The lift on an airfoil is primarily the result of its angle of attack. When oriented at a suitable angle, the airfoil deflects the oncoming air (for fixed-wing aircraft, a downward force), resulting in a force on the airfoil in the direction opposite to the deflection. This force is known as aerodynamic force and can be resolved into two components: lift and drag. Most foil shapes require a positive angle of attack to generate lift, but cambered airfoils can generate lift at zero angle of attack. This "turning" of the air in the vicinity of the airfoil creates curved streamlines, resulting in lower pressure on one side and higher pressure on the other. This pressure difference is accompanied by a velocity difference, via Bernoulli's principle, so the resulting flow field about the airfoil has a higher average velocity on the upper surface than on the lower surface.
Chord line may refer to:
a straight line connecting the leading and trailing edges of an airfoil.
The straight line drawn from the leading to trailing edges of the airfoil is called the chord line. The chord line cuts the airfoil into an upper surface and a lower surface. If we plot the points that lie halfway between the upper and lower surfaces, we obtain a curve called the mean camber line.
The angle of incidence is a figure about the geometry of the plane. The angle of attack is how the wing is oriented to the wind.
Yaw is induced by a moveable rudder-fin. The movement of the rudder changes the size and orientation of the force the vertical surface produces. Since the force is created at a distance behind the centre of gravity, this sideways force causes a yawing moment then a yawing motion. On a large aircraft there may be several independent rudders on the single fin for both safety and to control the inter-linked yaw and roll actions.
Using yaw alone is not a very efficient way of executing a level turn in an aircraft and will result in some sideslip. A precise combination of bank and lift must be generated to cause the required centripetal forces without producing a sideslip.
Pitch is controlled by the rear part of the tailplane's horizontal stabilizer being hinged to create an elevator. By moving the elevator control backwards the pilot moves the elevator up (a position of negative camber) and the downwards force on the horizontal tail is increased. The angle of attack on the wings increased so the nose is pitched up and lift is generally increased. In micro-lights and hang gliders the pitch action is reversed—the pitch control system is much simpler so when the pilot moves the elevator control backwards it produces a nose-down pitch and the angle of attack on the wing is reduced.
In this video module 8 question paper with module 8 answer are explained with theory. You can also prepare for module 8 quiz. Module 8 answer key and module 8 prashnottari also module 8 nishtha quiz answer and module 8 gatividhi and module 8 portfolio and module 8 notes can be refered.
#amemoduleexam #amemodules #dgcaameexam #easaanddgca #theoryofflight #aviation2304
Checkout our Other Videos :
Hello friends in this video we will discuss moduke 8 important questions with full theory.
if you like this video and want another video of more questions then like the video and comment below. Thank You.
An airfoil or aerofoil is the cross-sectional shape of a wing, blade (of a propeller, rotor, or turbine), or sail (as seen in cross-section).
An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag. Subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.
The lift on an airfoil is primarily the result of its angle of attack. When oriented at a suitable angle, the airfoil deflects the oncoming air (for fixed-wing aircraft, a downward force), resulting in a force on the airfoil in the direction opposite to the deflection. This force is known as aerodynamic force and can be resolved into two components: lift and drag. Most foil shapes require a positive angle of attack to generate lift, but cambered airfoils can generate lift at zero angle of attack. This "turning" of the air in the vicinity of the airfoil creates curved streamlines, resulting in lower pressure on one side and higher pressure on the other. This pressure difference is accompanied by a velocity difference, via Bernoulli's principle, so the resulting flow field about the airfoil has a higher average velocity on the upper surface than on the lower surface.
Chord line may refer to:
a straight line connecting the leading and trailing edges of an airfoil.
The straight line drawn from the leading to trailing edges of the airfoil is called the chord line. The chord line cuts the airfoil into an upper surface and a lower surface. If we plot the points that lie halfway between the upper and lower surfaces, we obtain a curve called the mean camber line.
The angle of incidence is a figure about the geometry of the plane. The angle of attack is how the wing is oriented to the wind.
Yaw is induced by a moveable rudder-fin. The movement of the rudder changes the size and orientation of the force the vertical surface produces. Since the force is created at a distance behind the centre of gravity, this sideways force causes a yawing moment then a yawing motion. On a large aircraft there may be several independent rudders on the single fin for both safety and to control the inter-linked yaw and roll actions.
Using yaw alone is not a very efficient way of executing a level turn in an aircraft and will result in some sideslip. A precise combination of bank and lift must be generated to cause the required centripetal forces without producing a sideslip.
Pitch is controlled by the rear part of the tailplane's horizontal stabilizer being hinged to create an elevator. By moving the elevator control backwards the pilot moves the elevator up (a position of negative camber) and the downwards force on the horizontal tail is increased. The angle of attack on the wings increased so the nose is pitched up and lift is generally increased. In micro-lights and hang gliders the pitch action is reversed—the pitch control system is much simpler so when the pilot moves the elevator control backwards it produces a nose-down pitch and the angle of attack on the wing is reduced.
In this video module 8 question paper with module 8 answer are explained with theory. You can also prepare for module 8 quiz. Module 8 answer key and module 8 prashnottari also module 8 nishtha quiz answer and module 8 gatividhi and module 8 portfolio and module 8 notes can be refered.
#amemoduleexam #amemodules #dgcaameexam #easaanddgca #theoryofflight #aviation2304
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