[greenfire]

If somebody help me about this project (About Matlab), I'll be very much happy

Given is a quasi-onedimensional flow field, described by an equation for the radius
R = ln{x+2 + √[(x+2)2 + 1]}
The area is, obviously, A = π R2 . The flow is assumed to be compressible, inviscid and unsteady,
being given by the corresponding Euler equations. Assuming that the flow field is purely supersonic
(supersonic inflow at x=0, supersonic outflow at x=2), solve the governing equation using a simple
explicit method. The Mach number at the inflow is Min = 1.5; the total temperature To = 300 K, the
total pressure Po = 0.1 MPa.

1. Determine the physical inflow conditions from NACA 1135 report.

2. Determine the physical outflow conditions using the same report.

3. Discuss the numerical boundary conditions at both inflow and outflow.

4. Compute the flow field using the above equations.

5. Compare your results with the theory.

Bonus Project

Assume that there is a compression shock at AS = 11.134; the corresponding pressure at the outflow is
pout,S = 0.5595 Po . Remember, you have to use in this case flux vector splitting!
Repeat 1. - 5.