Projects:EASA PPL/Principles of Flight: Difference between revisions
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* Terminology: | |||
** Chord line: line from leading edge to trailing edge | |||
** Camber line: halfway between upper and lower surface (start: leading edge / end: trailing edge) | |||
** Camber: curvature of camber line (distance between camber line and chord line) | |||
** angle of attack (alpha): angle between chord line and free flow | |||
** pitch angle (theta): | |||
** flight path angle (gamma): | |||
** theta = gamma + alpha | |||
** angle of incidence: angle between chord line and fuselage (Anströmwinkel) | |||
** Induced angle of attack: result of downwash, due to tip vortices | |||
** Effective angle of attack: angle between chord and actual local airflow | |||
** Load factor: lift / weight (max for utility aircraft = 4.4) | |||
* Bernoulli | |||
** Ptot = Pstat + Pdyn | |||
** Pdyn = 1/2 * rho * V² | |||
* Wing aspect ratio: ratio between wing span and mean geometric chord | |||
*Lift: | |||
**Lift = C<small>Lift</small> * Pdyn(aka q) * S<small>Area</small> | |||
**Lift = C<small>Lift</small> * (1/2 * rho * V²) * S<small>Area</small> | |||
**Coefficient of lift: | |||
***X Axis = Angle of Attack | |||
***Y Axis = Coefficient of liftb [[File:Lift curve.svg|ohne|mini]] | |||
*Drag: | |||
**Induced drag: result of creating lift | |||
**Parasitic drag: | |||
***Form drag: due to shape | |||
***Skin friction drag: surface roughness | |||
***Interference drag: created at junction of 2 bodies of the aircraft | |||
***DragP = C<small>Drag</small> * Pdyn * S | |||
***DragP = C<small>Drag</small> * 1/2 * rho * V² * S | |||
*Lift + Weight + Thrust + Drag | |||
*Stall | |||
**Stall speed in a turn: VStallInTurn = VStallStraight * sqrt( 1 / cos (phi) ) | |||
*Propeller | |||
**Gyroscopic precession - pitch and yaw | |||
Latest revision as of 17:53, 22 January 2023
- Terminology:
- Chord line: line from leading edge to trailing edge
- Camber line: halfway between upper and lower surface (start: leading edge / end: trailing edge)
- Camber: curvature of camber line (distance between camber line and chord line)
- angle of attack (alpha): angle between chord line and free flow
- pitch angle (theta):
- flight path angle (gamma):
- theta = gamma + alpha
- angle of incidence: angle between chord line and fuselage (Anströmwinkel)
- Induced angle of attack: result of downwash, due to tip vortices
- Effective angle of attack: angle between chord and actual local airflow
- Load factor: lift / weight (max for utility aircraft = 4.4)
- Bernoulli
- Ptot = Pstat + Pdyn
- Pdyn = 1/2 * rho * V²
- Wing aspect ratio: ratio between wing span and mean geometric chord
- Lift:
- Lift = CLift * Pdyn(aka q) * SArea
- Lift = CLift * (1/2 * rho * V²) * SArea
- Coefficient of lift:
- X Axis = Angle of Attack
- Y Axis = Coefficient of liftb
- Drag:
- Induced drag: result of creating lift
- Parasitic drag:
- Form drag: due to shape
- Skin friction drag: surface roughness
- Interference drag: created at junction of 2 bodies of the aircraft
- DragP = CDrag * Pdyn * S
- DragP = CDrag * 1/2 * rho * V² * S
- Lift + Weight + Thrust + Drag
- Stall
- Stall speed in a turn: VStallInTurn = VStallStraight * sqrt( 1 / cos (phi) )
- Propeller
- Gyroscopic precession - pitch and yaw
