I develop this document while studying for my EASA ATPL exams. To accomplish this I studied the Oxford Manual and did the Aviation Exam database. The information is brief and easy to read. I believe it contains all the information you will need to pass your exam. I hope you like it and can use it t...
BIG Thanks and good luck Captain! see you in the sky...
By: danielafilipacouto • 3 year ago
By: ThePilotPT • 2 year ago
Translated by Google
Hello Daniela! Thank you very much and good flights;) I'll see you upstairs!!!
By: lucasesposito • 3 year ago
By: ThePilotPT • 2 year ago
BIG Thanks and good luck Captain! see you in the sky...
By: timschneider • 3 year ago
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THE
PILOT
Principles
of flight
ATPL
STUDENT
pilot
resume
all info you need to pass atpl exams
, POF
General:
Bernoulli: Sum of all energy constant
3
Temperature ~ density(rho)[kg/m ]
Density ∝ mass
Density ∝ pressure
Density does not vary in venturi
Density decrease as humidity increase
Temp ↑ mass flow ↓
2
Dynamic pressure [q]( N/m )
1 2
= / 2 ρV(TAS)
Dynamic press = 0 when speed = 0
Static + dynamic = constant
p/(rho*T) = Constant
• SI units:
- Weight (Newton) = Force = Mass(kg) x acceleration
- Power (Nm/s) = Watts (W) Force x distance ÷ time (J/s) [There is time]
- Work = Joule
2
- Force [kg.m/s ]= m x a
2
- Wing loading[W/S](N/m ): Weight of aircraft ÷ area of the wings
• Density decrease with increase in humidity (Dry air = better performance)
• Mean geometric chord: Wing area ÷ wing span
Difference between MAC & mean camber line
Relative thickness: Expressed in % chord
Symmetrical airfoil: 0 camber, mean camber line = chord line
& lift characteristics as the actual wing
• Aeroplane AOA: Angle between speed vector & longitudinal axis
Wing AOA: Angle between longitudinal axis & wing root chord line
Angle of incidence: Angle between wing root chord line & longitudinal axis
Dihedral angle:
- Angle between wing plane & the horizontal with aeroplane in an unbanked , level condition
- Angle between the 0.25 chord line of the wing and the lateral axis
• Lift & drag forces depend on the pressure distribuition around the aerofoil cross section
• Lift = Component of total aerodynamic force perpendicular to the undisturbed airflow
2D airflow over an aerofoil
o
• Typical C L /C D ratio: Max at angle of attack of 4
• Lift:
- Upwash ahead of the wing & downwash behind
- Downwash increase: Lift generated by the aerofoil increases
- Upper surface produces greatest proportion of lift at all speeds
- Generated when the flow direction of a certain mass of air is changed
• Stagnation point:
- Static pressure maximum value
- Relative velocity = 0
• AOA
- Decrease: Stagnation point moves forward /up, lowest pressure(CP) moves aft, COP moves aft
- Increase: Stagnation point moves down, lowest pressure(CP) moves forward, COP moves forward until crit AOA
• Aerodynamic centre of an aerofoil:
- Approx 25% chord irrespective/independent of AOA
- Assume no flow separation, pitching moment coefficient does not change with carying angle of attack
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