Aerodynamics Self-Assessment Exercise 4
16 Questions
2 Views

Choose a study mode

Play Quiz
Study Flashcards
Spaced Repetition
Chat to lesson

Podcast

Play an AI-generated podcast conversation about this lesson

Questions and Answers

What determines the magnitude of the lift and drag forces of a wing cross-section?

  • The wing shape
  • The pressure distribution around the wing (correct)
  • The angle of attack
  • The airspeed

    • At what angles of attack are the lift and drag forces of a wing cross-section normal to each other?

  • 45 degrees only
  • 0 degrees only
  • 90 degrees only
  • They are never normal to each other (correct)

    • What happens to the pitching moment when trailing-edge flaps are deployed in level flight?

  • Dependent on the CG location
  • Nose-down
  • Remains unchanged
  • Nose-up (correct)

    • How does the induced drag and wing-tip vortices change with increasing angles of attack?

    <p>The wing-tip vortices and induced drag increase</p> Signup and view all the answers

    Which factor results in the induced angle of attack?

    <p>Downwash due to wing-tip vortices</p> Signup and view all the answers

    What effect do vortex generators have on wing-tip vortices?

    <p>Diminish wing-tip vortices</p> Signup and view all the answers

    At a constant IAS and mass in level flight during flap selection, what happens?

    <p>Both Cl and Cd increase</p> Signup and view all the answers

    What causes pitch up at low speed?

    <p>Spanwise flow on a swept-back wing</p> Signup and view all the answers

    Regarding the boundary layer, which of the following statements is correct?

    <p>The turbulent boundary layer generates less skin friction than the laminar boundary layer</p> Signup and view all the answers

    Which of the following statements is correct?

    <p>The stagnation point moves downward on a wing profile as the angle of attack increases</p> Signup and view all the answers

    The most important advantage of the turbulent boundary layer over the laminar boundary layer is:

    <p>It reduces skin friction</p> Signup and view all the answers

    For a positively cambered aerofoil when Cl is zero, what happens to the pitch moment?

    <p>Negative (pitch-down)</p> Signup and view all the answers

    What does Winglets improve in an aeroplane's performance?

    <p>Decrease the induced drag</p> Signup and view all the answers

    The direction of spanwise flow is from:

    <p>The top of the wing to beneath the wing via the leading edge</p> Signup and view all the answers

    The CP of a positive cambered wing at an increasing angle of attack will:

    <p>Move aft</p> Signup and view all the answers

    What happens aft of the transition point between laminar and turbulent flow?

    <p>The mean speed increases and the surface friction increases</p> Signup and view all the answers

    More Like This

    Use Quizgecko on...
    Browser
    Open
    Browser
    Browser