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April 13th, 2017, 09:00 AM
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Re: PGECET Old Exam Papers

Post Graduate Engineering Common Entrance Test Questions with Solutions available. Candidates who want to download Telangana and Andhra Pradesh PGECET entrance exam Previous year question paper with solutions from PGECET official site.

Test is of two hour duration with 120 multiple choice objective type questions, carrying one mark for each question.

The cut-off mark in the Common Entrance Test is 25%, in case of SC/ST there is no minimum marks.

Get PGECET Old Exam Papers:




PGECET Old Exam Papers Aerospace:

9. Which of these methods is not a step method to solve ordinary differential equation ?
(A) Runge Kutta method (B) Euler method
(C) Taylor’s method (D) Milne method

10. The order of convergence of bisection method is
(A) Linear (B) quadratic (C) cubic (D) None

11. In reversible adiabatic process of a perfect gas
(A) Stagnation pressure and stagnation temperature are constant.
(B) Only Stagnation temperature is constant.
(C) Only stagnation pressure is constant.
(D) Stagnation pressure and stagnation temperature are not constant.

12. Entropy of perfect gas increases with
(A) Stagnation Pressure Loss (B) Velocity change
(C) Static pressure change (D) Stagnation temperature change

13. For a normal shock with the upstream Mach number tends to infinity, the resulting downstream Mach number for perfect gas with specific heat ratio 1.4 is
(A) 1 (B) 0 (C) 0.378 (D) Infinity

14. Estimate the Mach number for an aircraft flying in the air at a speed of 1000 kmph, at standard sea level temperature 15°C.
(A) 1.0 (B) 0.817 (C) 0.917 (D) 1.917

15. Air at a stagnation state of 3 atm and 300 K is accelerated to 200 m/s. Determine the Mach number of the flow.
(A) 0.596 (B) 0.317 (C) 1.0 (D) 0.0

16. Consider a flow through convergent-divergent nozzle, if the exit pressure is less than the back pressure, the nozzle is said to be
(A) Under expanded (B) Over expanded
(C) Correctly expanded (D) Choked

17. A convergent-divergent nozzle is designed to operate with exit Mach number of 1.75. The nozzle is supplied from an air reservoir at 68 × 105 N/m2 (abs). The exit to throat area ratio is 1.386. The exit Mach number when the nozzle just chokes is 0.48. What is the maximum back pressure to choke the nozzle ?
(A) 68 atm (B) 58 atm (C) 48 atm (D) 38 atm

18. A Mach number 2.0 nozzle is run by a settling chamber with air maintained at 300 K. The air is discharging to an environment at atmospheric pressure. Determine the settling chamber pressure required to run nozzle at correctly expanded state.
(A) 7.82 atm (B) 2.24 atm (C) 1.42 atm (D) 5.28 atm


19. The coefficient of pressure at a stagnation point in the compressible flow with freestream Mach number as M is
(A) 1 (B) 1+ M2
/4+ M4
/40
(C) M2
/2 (D) M2
/2 + M

20. For an airfoil at 12° angle of attack, the normal and axial force coefficients are 1.2 and 0.03, respectively. The lift and drag coefficients respectively are
(A) 1.18 and 0.279 (B) 1.18 and –0.279
(C) –1.18 and –0.279 (D) 0.0 and 0.0

21. Irrotational, incompressible flow has both velocity potential and stream function that should satisfy
(A) Euler equation (B) Laplace equation
(C) Bernoulli equation (D) Energy equation

22. Circulation around any closed curve in a uniform flow is
(A) Unity (B) Finite (C) Zero (D) Infinity

23. For source flow, the velocity potential lines are
(A) Radial lines (B) Circles (C) Straight lines (D) Elliptical

24. For what bodies the skin friction drag accounts for the major portion of the total drag and the wake drag is very small ?
(A) Bluff body (B) Automobiles
(C) Streamlined body (D) Pipes

25. An aircraft of mass 1500 kg in a steady level flight. If the wing incidence with respect to the freestream flow is 3 deg, what could be the aerodynamic efficiency of the aircraft ?
(A) 99 (B) 59 (C) 19 (D) 29

26. The semi-span of a rectangular wing of planform area 8.4 m2 is 3.5 m. What could be the aspect ratio of wing ?
(A) 10.83 (B) 8.83 (C) 3.85 (D) 5.83

27. For 2D wedge shaped body in supersonic flow with an attached oblique shock, an increase in freestream Mach number will cause the oblique shock wave
(A) To move away from the body (B) To move closer to the body
(C) To remain unaffected (D) To become normal shock wave

28. At a given point on the surface of an airfoil, the pressure coefficient is –0.3 at very low speeds. If the freestream Mach number is 0.6, calculate the pressure coefficient at this point.
(A) –0.375 (B) 0.375 (C) 2.67 (D) –2.67


Here I’m attaching PDF of PGECET Old Exam Papers Aerospace:
Attached Files
File Type: pdf PGECET Old Exam Papers Aerospace.pdf (278.8 KB, 71 views)


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