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Examination Question of AERODYNAMICS - II - BPUT - 2017

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Registration No: Total Number of Pages: 02 B.Tech. PAE5I102 5th Semester Regular Examination 2017-18 Aerodynamics-II BRANCH: AERO Time: 3 Hours Max Marks: 100 Q.CODE: B168 Answer Question No.1 and 2 which are compulsory and any four from the rest. The figures in the right hand margin indicate marks. Q1 a) Answer the following questions: multiple type or dash fill up type If ρ is expressible as a function of p only, the fluid having this characteristic are called ___________________. b) When M* is the ratio of local flow speed and critical speed of sound, then it is called as the _______________________. c) In a stream tube the area – velocity relation can be expressed as ________________. d) In a nozzle when pe<pb, the nozzle is said to be ______________________. e) The Mach number behind a normal shock is always _____________________. f) The flow through a normal shock is _____________________. a)One Dimensional b)Two Dimensional c)Three Dimensional d) All of the above. g) _______________ is a graphical representation of oblique shock properties. h) The rate of change of stream properties along a Rayleigh line is a function of the rate of change of stagnation temperature. (True/False) i) Which of the following statement is NOT TRUE across an oblique shock wave? (A) Static temperature increases, total temperature remains constant. (B) Static pressure increases, static temperature increases. (C) Static temperature increases, total pressure decreases. (D) Static pressure increases, total temperature decreases. j) Use of ____________________ not only increases Mcrit, but also reduces the rate of drag coefficient in transonic flow. (2 x 10)

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Q2 a) b) c) d) e) f) g) h) i) j) Answer the following questions: Short answer type Write continuity equation for a 1-D flow. What is internal energy for a gas? Explain. Write equation for relations between stagnation pressures, density with Mach number What do you mean by steady level flight? Define Rayleigh flow Write about shock boundary layer interactions? Write the difference between the flow over the wedge and cone? What are the qualitative aspects of hypersonic flow? Write about over expanded flow at the nozzle exit? Write about intersection of shocks? (2 x 10) Q3 a) b) Obtain an equation for continuity? Write continuity equation for 1- D flow? Air flow is discharged to atmosphere at sea level through a sonic nozzle' If the air storage at the reservoir is 40 x 10s N/m2, determine the pressure, temperature and density at the exit of the nozzle- Assume that the reservoir air is at sea level temperature? (10) (5) Q4 a) b) Derive the Rayleigh supersonic pitot formula? A Pitot tube is inserted in to an air flow of Mach 2 where the static pressure is 1 atm. Calculate the total pressure measured by the tube and. the loss of total pressure experienced. (10) (5) Q5 a) b) Write about intersection of shocks, Mach reflection? Explain the concept of prandtl-Meyer expansion around a convex corner and represent in the Hodograph plane. (10) (5) Q6 a) Explain the procedure to obtain supersonic nozzle contour for a given Mach number using method of characteristics. Explain about whitcombs transonic area rule? (10) b) (5) Q7 a) b) Write about intersection of shocks, Mach reflection? A supersonic flow with M1 = 1.5 , p1= 1 atm and T1= 288k is expanded around a sharp corner through a deflection angle 150 .calculate T2,V2,and the angles that the forward and rearward Mach lines with respect to the upstream flow direction . (10) (5) Q8 a) Give a brief outline of operation of supersonic wind tunnels employing convergent -divergent nozzles? The nozzle of a supersonic wind tunnel has an exit to throat area ratio of 6.79 when the tunnel is running, a pitot tube mounted in the test section, measures 1.448atm, what is the reservoir pressure for the tunnel. (10) Explain principle of limited upstream influence in supersonic flow? Calculate L/D ratio for flight conditions of Mach 2.0 at an altitude of 11km. for these conditions the wing angle of attack is 0.035rad, assume chord length of airfoil is 2.2m. (10) (5) b) Q9 a) b) (5)

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