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model 8.2
22問 • 1年前
  • Slem Abdo
    • 通報

    問題一覧

  • 1

    As an incompressible fluid flows through a duct of varying cross sectional area, the mass flow rate remains constant. this is defined as

    the principle of continuity.

  • 2

    Ground speed can be determined

    by the vector sum of the aircraft's true airspeed and the current wind speed and direction.

  • 3

    ●The resultant airflow that affects the wing is made

    by the relative horizontal and vertical airflow components.

  • 4

    The chord line of a wing is a line that

    runs from the centre of the leading edge of the wing to the trailing edge.

  • 5

    Angle of attack is

    the angle between oncoming air (or relative airflow) and the chord line of the wing.

  • 6

    An increase in the angle of attack will cause

    the centre of pressure to move forward

  • 7

    ●when trailing edge flaps are deployed, the camber and the angle of attack are both

    increased

  • 8

    ●An increase in aircraft weight

    will increase the stall speed.

  • 9

    The aero foil produces zero lift at a certain

    negative angle of attack

  • 10

    Drag acts in a direction parallel with the relative airflow, and is therefore

    always perpendicular to lift (where generated).

  • 11

    the aspect ratio of a wing is the ratio of

    its span to its aerodynamic chord

  • 12

    ●Wing loading is calculated by

    weight divided by gross wing area.

  • 13

    Longitudinal dihedral angle is defined as

    the difference the angle of incidence of the mainplane and tailplane.

  • 14

    Wing tip vortices on conventional aeroplanes create

    additional drag and reduce lift.

  • 15

    Skin friction drag increases with

    increasing turbulent boundary layer.

  • 16

    Friction drag can be reduced by

    delaying the point at which laminar flow becomes turbulent.

  • 17

    Induced drag

    is greater at low aspect ratio wing.

  • 18

    Profile drag

    increases with the square of the IAS

  • 19

    If the weight of an aircraft is increased,

    minimum drag speed will increase

  • 20

    ●symmetrical aeorfoil, with all other things being equal, will stall

    at higher angle of attack as a cambered aerofoil, but will produce less lift at any given angle of attack bellow th

  • 21

    stall

    is the inability of the air to travel over the surface of the wing against the adverse pressure gradient behind the point of minimum pressure.

  • 22

    Vortex generators

    move the transition point forwards towards the leading edge of the wing.

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    問題一覧

  • 1

    As an incompressible fluid flows through a duct of varying cross sectional area, the mass flow rate remains constant. this is defined as

    the principle of continuity.

  • 2

    Ground speed can be determined

    by the vector sum of the aircraft's true airspeed and the current wind speed and direction.

  • 3

    ●The resultant airflow that affects the wing is made

    by the relative horizontal and vertical airflow components.

  • 4

    The chord line of a wing is a line that

    runs from the centre of the leading edge of the wing to the trailing edge.

  • 5

    Angle of attack is

    the angle between oncoming air (or relative airflow) and the chord line of the wing.

  • 6

    An increase in the angle of attack will cause

    the centre of pressure to move forward

  • 7

    ●when trailing edge flaps are deployed, the camber and the angle of attack are both

    increased

  • 8

    ●An increase in aircraft weight

    will increase the stall speed.

  • 9

    The aero foil produces zero lift at a certain

    negative angle of attack

  • 10

    Drag acts in a direction parallel with the relative airflow, and is therefore

    always perpendicular to lift (where generated).

  • 11

    the aspect ratio of a wing is the ratio of

    its span to its aerodynamic chord

  • 12

    ●Wing loading is calculated by

    weight divided by gross wing area.

  • 13

    Longitudinal dihedral angle is defined as

    the difference the angle of incidence of the mainplane and tailplane.

  • 14

    Wing tip vortices on conventional aeroplanes create

    additional drag and reduce lift.

  • 15

    Skin friction drag increases with

    increasing turbulent boundary layer.

  • 16

    Friction drag can be reduced by

    delaying the point at which laminar flow becomes turbulent.

  • 17

    Induced drag

    is greater at low aspect ratio wing.

  • 18

    Profile drag

    increases with the square of the IAS

  • 19

    If the weight of an aircraft is increased,

    minimum drag speed will increase

  • 20

    ●symmetrical aeorfoil, with all other things being equal, will stall

    at higher angle of attack as a cambered aerofoil, but will produce less lift at any given angle of attack bellow th

  • 21

    stall

    is the inability of the air to travel over the surface of the wing against the adverse pressure gradient behind the point of minimum pressure.

  • 22

    Vortex generators

    move the transition point forwards towards the leading edge of the wing.