In this summary you can find answers for the easa atpl exam in principles of flight. The notes are made from courses and exam questions. I used personally these notes to pass all exams.
• Units • Weight (dependent): Force = N = kg*m/s2
• Mass (independent to gravity): kg
• Energy: J = N*m
➡ Power: Watt = J/s = N*m/s
• Density (rho): Mass/Vol. = kg/m3 = 1,225kg/m3
• Pressure: Pa = N/m2
• Wing-load: kg/m2
• Newton’s Laws 1. Inertia: Body remain at rest unless external force
2. F=m*a
3. Actio=reactio: Each reaction equal and opposite reaction
• Pressure Bernoulli (TAS): Σ all energy const.: pT = pS + q
• Static pressure (pS): in all directions
• Dynamic pressure (q) = 1/2 *roh*v2
➡ IAS: 1/2 *roh*TAS2
Gas Equation: p*V = m*Rair*T
Equation continuity: mass flow const. = A*roh*V —> v1*A1 =v2*A2
Aerodynamic
Drag
• Aerofoil • Camber: distance camber line & chord line Lift Total reaction
• line: between upper & lower surface
LE TE
• Chord Line: straight between LE & TE CP
• Thickness: max. thick/ chord
SP (v=0)
• AoA: between Chord line & RAF
+ SP down, CP forw
• Center of Pressure (CoP): on chord line: aerodynamic force: total lift act on
➡ Symmetric airfoil: no change aoa; @25% chord
• Wings • Avg. Chord (MGC): Area/Span
• AR: Span/Avg. Chord = Span^2/Area
• Taper Ratio: Tip chord/ Root chord
• Sweep α: wing inclined to lateral axis
➡ Di (up)-/Anhedral (down) α
• α of incidence (fixed): chord line & longitudinal axis
• Aerodynamic centre (fixed): Pitching moment acts on; no AoA
• Lift Component of total force, perpendicular to airflow
➡ Greater than Drag: L = 1/2* roh* CL* S *v2
• CL: Lift per area & dyn. Pressure
➡ depends: AoA, Camber, (thickness)
• Polar curve: CL/CD-Ratio (2,5…,1)
1. Min. CD (value of drag coefficient)
2. Best: VMD & min. glide angle (CL/CD max.)
➡ max. lift @4° AoA = VMD
3. Min. sink
4. Slow speed | close to stall
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