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MCQ Part 7 (in Hindi)
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Mcqs

Priya Malani
Hello! BTech(Aerospace),Cleared Afcat(2 times),Cry Volunteer,Stem Education Enthusiast.

U
Unacademy user
thanku so much mam.. boht kuch seekhne ko mila
Anupama Rani
5 months ago
Most welcome
  1. MCQ's for flight mechanics by priya malani


  2. ABOUT ME XBachelors in Technology in Aerospace SRM UNIVERSITY Cleared AFCAT 11-2017 Cleared AFCAT 1-2018 xGate Aspirant Educator on Unacademy


  3. Hello! I am Priya Malani I am here because I love to share my knowledge. You can find me at: @https://unacademy.com/user/priyamalani96-4980


  4. MCQ's for flight mechanics by priya malani


  5. 1. STALL


  6. 1-Low speed pitch up is caused by the? a.wing tip vortex b. Mach trim system Spanwise flow on a swept forward wing d. Spanwise flow on a swept forward wing


  7. 1-Low speed pitch up is caused by the? a wing tip vortex b. Mach trim system Spanwise flow on a swept forward wing Spanwise flow on a swept forward wing.


  8. ANSWERS: Airflow passing over swept back wings tends to migrate outwards from the roots towards the tips, producing a thick, low energy boundary layer in the wing tip region. As angle of attack is increased this low energy boundary layer separates easily from the upper surfaces causing the wing tips to stall before the roots. Swept back wings are therefore prone to tip stall due to separation of flow energy boundary layer at the tips. In the cause of swept forward wings the airflow tends to migrate towards the wing roots making tip stall much less likely. Wing tip vortices and mach trim system are not directly related to low speed stall or pitch up. So low speed up is caused span wise flow on a swept back wing


  9. 2-For an aeroplane with one fixed value of VA the following applies. VA is? aThe speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW b. The maximum speed in smooth air. at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor. d. just another symbol for rough air speed


  10. 2-For an aeroplane with one fixed value of VA the following applies. VA is? a.The speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW. b. The maximum speed in smooth air. The speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor. d. just another symbol for rough air speed


  11. 3-The critical angle of attack? a. Changes with an increase in gross weight b. Remains unchanged regardless of gross weight. c.Increase if the CG is moved forward. d decrease if the CG Is moved aft. S .


  12. ANSWERS: The critical angle of attack is the angle at which the separation of boundary layer and aerodynamic stall begin. At subsonic airspeeds, this angle is determined only by aerofoil cross section, the aerofoil plan form and its surface condition. So the critical angle of attack remains unchanged regardless of gross weight


  13. ANSWERS: When a straight winged aircraft stalls its centre of pressure will suddenly move aft. This will cause the aircraft to pitch nose down


  14. Thanks! Any questions? You can find me at: @ https://unacademy.com/user/priyamalani96-4980


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