Aerodynamics – exam 20-06-2014 (only for student who passed

the midterm exam)

Basic part

1. Define an isentropic process. Provide the relation between pressure and

density in the isentropic process.

2. In the density/pressure plane, draw the plot of the thermodynamic process

corresponding to a shock wave. Can an expansion (rarefaction) shock wave
appear in real flows? Explain your answer.

3. Make a careful plot of velocity and temperature profiles in the laminar

compressible boundary layer at the thermally isolated wall.

4. Make a careful and precise plot of a supersonic flow past a flat plate at

nonzero angle of incidence.

Advanced part

5. Make a careful and precise plot of the oblique shock polar. Using this plot

explain how the angle of inclination of the shock wave is determined if the
angle of flow deflection is given. Mark on the picture the case of flow
corresponding to the maximal inclination angle.

6. Make a precise plot (and comment it properly) showing how the drag

coefficient C

D

depends on the Mach number M

∞

.

Time: 60 minutes