ATF EXAM 2025 QUESTIONS WITH CORRECT ANSWERS

ATF EXAM 2025 QUESTIONS WITH
CORRECT ANSWERS
4 |Forces |Acting |on |an |Aircraft |- |VERIFIED |ANSWER✔✔-Lift, |weight, |thrust, |drag



Bernoulli's |Theorem |- |VERIFIED |ANSWER✔✔-P+1/2(roh)V^2= |constant |

Or

Pressure |+ |1/2 |x |air |density |x |velocity |squared |= |constant

Or

Static |pressure |+ |dynamic |pressure |= |constant



2 |Types |of |Pressure |- |VERIFIED |ANSWER✔✔-Static |pressure |- |stationary

Dynamic |pressure |- |air |in |motion

If |one |increases, |the |other |decreases.



Lift |- |VERIFIED |ANSWER✔✔-If |an |aircraft |accelerates, |it |is |no |longer |at |a |constant. |When |there |is |an |
increase |in |velocity |over |an |aerofoil, |there |is |a |decrease |in |pressure |over |that |aerofoil |(static). |
Generated |by |air |travelling |faster |above |the |aerofoil |than |below |it.



Downwash |- |VERIFIED |ANSWER✔✔-An |increase |in |pressure |underneath |the |aerofoil. |Air |deflected |
downwards.



Newton's |3 |Laws |- |VERIFIED |ANSWER✔✔-Inertia: |objects |in |motion |stay |in |motion, |objects |at |rest |
stay |at |rest.

F=ma: |the |degree |to |which |an |object |changes |its |state |of |motion |is |proportional |to |the |force |applied.

F=-F: |every |action |has |an |equal |and |opposite |reaction.



Angle |of |Attack |- |VERIFIED |ANSWER✔✔-Angle |made |between |the |wing |chord |and |the |relative |airflow.

, Centre |of |Pressure |- |VERIFIED |ANSWER✔✔-If |we |consider |all |distributed |pressure |to |be |equivalent |to
|a |single |force, |this |force |will |act |through |a |straight |line. |Where |this |line |cuts |the |chord |of |an |aerofoil

|is |the |centre |of |pressure.




CP |Movement |- |VERIFIED |ANSWER✔✔-As |AOA |increases, |the |point |of |the |lowest |CP |moves |forward. |
This |increases |the |adverse |pressure |gradient |and |area |of |surface |friction. |This |causes |the |air |to |
become |slightly |turbulent. |As |the |wing |passes |the |stall |angle |(17) |CP |moves |rearward |rapidly.



Loss |of |Lift |- |VERIFIED |ANSWER✔✔-As |AOA |increases, |the |point |of |the |lowest |CP |moves |forward. |As |
the |wind |passes |the |stall |angle, |CP |rapidly |moves |rearward. |The |wing |drops |at |stall |because |CP |
moves |ahead |of |CG, |lift |on |top |is |lost, |resulting |in |more |weight |in |front |of |the |aerodynamic |centre.



Relative |Airflow |- |VERIFIED |ANSWER✔✔-Always |parallel |with |and |opposite |to |the |flight |path |of |the |
A/C. |The |flight |path |angle |and |the |angle |of |the |wing |(AOA) |may |not |be |the |same.



Angle |of |Incidence |- |VERIFIED |ANSWER✔✔-Fixed |angle |between |the |wing |chord |and |the |longitudinal |
axis |of |the |aircraft.



Drag |- |VERIFIED |ANSWER✔✔-Force |which |opposes |the |forward |motion |of |the |aircraft. |Induced |drag |
and |parasite |drag.



Induced |Drag |- |VERIFIED |ANSWER✔✔-By-product |of |list. |As |the |pressure |differential |increases, |the |
stronger |the |vortex |generated. |At |the |strength |of |the |vortex |increases, |more |induced |drag |is |
produced.



Parasite |Drag |- |VERIFIED |ANSWER✔✔-Made |up |of |all |the |other |drag. |Interference |drag, |profile |drag, |
form |drag, |and |skin |friction.



Pressure |Drag |- |VERIFIED |ANSWER✔✔-Results |from |the |pressure |differential |between |the |fire |and |aft
|sides |of |an |A/C |(produces |a |wake).




Interference |Drag |- |VERIFIED |ANSWER✔✔-Pressure |drag |created |by |the |intersection |between |the |two
|parts |of |an |aircraft |(wing |strut).