Gujarat Technological University 2010-5th Sem B.Tech Aeronautical Engineering - in - EMBER,Computational Fluid Dynamics-I - Question Paper
The 5th semester of the Gujarat Technological University in the stream of Aeronautical Engineering has 7 subjects. The paper trend are all the identical and 1 has the subsequent subjects Composite Materials and Smart Structures, Flight Mechanics, Fundamentals of Turbo M/cs, Management-II, Aircraft Structure-II, Computational Fluid Dyanamics-1 and Operation & Maintenance of Aircraft. The paper has five ques. of 14 marks each, making the total marks of the paper 70. The ques. paper is to be answered within three hours.
beneath are attached Computational Fluid Dyanamics-1 ques. paper.
GUJARAT TECHNOLOGICAL UNIVERSITY
B.E. Sem-Vth Examination December 2010
Seat No. Enrolment No.
Subject code: 150104 Sub Name: Computational Fluid Dynamics-I Date: 18 /12 /2010 Time: 03.00 pm - 05.30 pm
Total Marks: 70
Instructions:
1. Attempt all questions.
2. Make suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.
Q.1 (a) Derive the energy equation for a viscous flow with heat transfer in non 07 conservation form.
(b) Justify CFD is a research tool. Write and explain the steps involved in CFD 07 process.
Q.2 (a) What is the difference between the Eulers model and Navier stokes model of 07 equations? Write the generic form of Navier Stokes model.
(b) Explain the supersonic flow over the nose of a blunt body. Write a short note on 07 shock capturing method.
OR
(b) Consider the irrotational, 2-D, inviscid, steady flow of a compressible gas. The 07 flow field is slightly perturbed from free seam like flow over a thin profile. Find the roots of equations involved in such kind of flow problem using Cramers rule and Eigen method.
Q.3 (a) Distinguish between the basic discretization techniques. Derive the expression for 07 1st order forward, 1st order rearward and 2nd order central difference equation with respect to x.
(b) Explain the domain and boundaries for the solution of parabolic equation in 2-D. 07 also explain the steady boundary layer flows over a body.
OR
Q.3 (a) Derive the differential equation to unsteady 1-D heat conduction equation. Also 07 define the accurate solution and precise solution.
(b) Write a short note on Lax Wendroff method and gives its stability criteria. 07
Q.4 (a) Differentiating between explicit approach and implicit approach for the solution of 07 difference equations. Formulate the explicit form for 1-D heat conduction equation.
OR
Q.4 (a) Describe Mac Cormark multi-step method. 07
(b) Consider the viscous flow of air over a flat plate. Variation in velocity with respect 07 to y is given as: u=1582(1-e-y/L). Where L= 1 unit and p=3.37*10-7slug/ (ft.s). y is from 0 to 0.3 in the steps of 0.1. Find the percentage error in shear stress, involved in 1st ordered and 2nd ordered difference compared to exact solution.
Q.5 (a) Draw and explain the subsonic-supersonic flow through the C-D nozzle and also show the variation in properties along the length of nozzle (b) Derive the momentum equation for the 2-D subsonic supersonic flow through C-D nozzle.
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OR
Q.5 (a) How the boundary conditions and initial conditions are applied to the nozzle flow. (b) Why the governing equations are to be transformed into non dimensional form? Derive the momentum equation in non dimensional form for the nozzle flow.
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| Earning: Approval pending. |
