Summary Ace the technical pilot interview

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ISBN-10 0071793860 ISBN-13 9780071793865
133 Flashcards & Notes
2 Students
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This is the summary of the book "Ace the technical pilot interview". The author(s) of the book is/are Gary V Bristow. The ISBN of the book is 9780071793865 or 0071793860. This summary is written by students who study efficient with the Study Tool of Study Smart With Chris.

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Summary - Ace the technical pilot interview

  • 1 Aerodynamics

  • Maximum glide range

    Optimal angle of attack and corresponding minimum drag speed (VIMD)

  • 1.1 Forces/Aerofoil Lift Drag weight

  • Effect of weight on glide range

    Does not vary with weight; glide same distance as light a/c but faster

  • Chord line/Chamber line

    Straight line from the leading edge to the trailing edge

    Line from leading edge to trailing edge of equidistance on upper and lower surface

  • Lift formula

    1/2 R v2 S Cl

  • what is coefficient of lift

    Lifting ability of a particular wing. Depends on shape/AoA

  • Center of Pressure + movement

    Single point acting on the wingchord at right angles to relative flow through which the wings lifting force is produced

  • Aspect Ration (high/low)

    high: high lift (gliders

    low: lower lift but capable of higher speeds

  • 2 major types of drag

    Profile and Induced

  • Profile drag consists of?

    Form or Pressure Drag

    skin-friction Drag

    Interference Drag

  • minimum drag speed VIMD

    Speed at which induced and profile drag are equal - > best lift to drag ratio

     

  • Maximum endurance (graph)

    best lift to drag ratio: VIMD

  • Forward CG is limited to

    Not too nose heavy so that the horizontal tailplane has a sufficient turning moment

    Pitch control not compromised

    Minimal horizontal tailplan deflection (minimal drag/elevator range maintained)

  • CG forward

    Longitudinal stability is increase because the aircraft is nose heavy

    Pitch control is reduced (high stick forces due to the aircraft's long tailplane moment arm)

    Large balancing download necessary from the horizontal tailplane by deflecting the elevator

    -Increase AoA

    -Increased stalling speed (balancing download on taiplane increases aircraft wieght)

    -less elevator is avail for pitch control

    -in-flight minimum speeds are also restircted (lack of elevator)

    //A/C is heavy and less responsive to handle in flight and requires larger and heavier control forces for t/o and land

  • CG aft

    Longitudinally unstable because it is too  tail heavy for the horizontal tailplane turning moment to balance

    pitch control increased (light forces due to short tailplane arm)

    Large balancing upload necessary from horizontaltailplane

    -Decreased AoA

    -Lower stalling speed (less weight from upload balance)

    -if elevator is required for balance trim, less is avail for pitch control

    //A/C is effectively light and more responsive to handle in flight and requires smaller and lighter control forces

  • 1.5 Swept Wing

  • How does swept wing aid the increase in its critical Mach number?

    A swept wing makes the velocity vector normal (perpendicular) to the leading edge a shorter distance than the chordwise resultant. Since the wing is responsive only to the leading edge, the effective chordwise velocity is reduced. (wind persuaded to believe that it is flying slower than it actually is)

    Delays the airflow over the wing from going supersonic. Also thinner wing (chamber) = less profile drag

  • Advantages of Swept Wing

    High Mach cruise speeds

    Stability in turbulence

  • Disadvantages of Swept Wing

    Poor lift qualities

    Higher Stall speeds

    Speed instability (lower lift at slow speeds) - Speed unstable below VIMD back end of jet drag curve

    Wing tip stall

  • CP on swept wing

    moves inward and forward (due to wingtip stalling first) which creates a pitch up

    -washout or twist or bigger chamber delays this

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