incompressible laminar turbulent flat plate boundary layer besides the

Search for question

Question

Incompressible laminar/turbulent flat plate boundary layer
Besides the common assessed elements listed above, the boundary layer
study focusses on reinforcing certain elements of boundary layer theory,
specifically the self-similar Blasius solution for laminar boundary layers and
the law of the wall for turbulent flow. Extract the velocity profiles at a minimum
of two streamwise stations and post-process the data to map the numerical
results to the theoretical results. Useful additional plots and analyses would
Page 1
Computer Lab on Time Stepper Study
show the development of streamwise skin-friction, total skin-friction drag
coefficient, displacement thickness, momentum thickness, shape factor, etc.,
while always comparing and discussing theory with numerical results.
The underlying theories, first introduced either in AERO306 Aerodynamics or
MECH326 Engineering Fluid Mechanics, have been revised in lecture 5./nInviscid supersonic diamond- (or double-) wedge aerofoil
Besides the common assessed elements listed above, the study of supersonic
inviscid flow focusses on reinforcing supersonic shock and expansion theory.
As such, you are required to do the appropriate hand calculations to establish
the local Mach number, static pressure, etc. for each deflection of the flow and
compare with the numerical results. Inviscid flow implies solving the Euler
equations which offer correct solutions for shock and expansion. Consider the
wake angle carefully. In addition, lift and drag coefficients can be extracted
from the numerical data and compared with the theory. Useful additional
simulations would include establishing the minimum free-stream Mach number
for a given deflection angle to obtain an attached shock at the leading edge
(i.e. to first find a detached shock). Alternatively, find the required opening
angle & (see figure 1) for a given Mach number to observe a detached shock.
The underlying theories, first introduced either in AERO306 Aerodynamics or
MECH326 Engineering Fluid Mechanics, have been revised in lecture 5./nInviscid supersonic diamond- (or double-) wedge aerofoil
Besides the common assessed elements listed above, the study of supersonic
inviscid flow focusses on reinforcing supersonic shock and expansion theory.
As such, you are required to do the appropriate hand calculations to establish
the local Mach number, static pressure, etc. for each deflection of the flow and
compare with the numerical results. Inviscid flow implies solving the Euler
equations which offer correct solutions for shock and expansion. Consider the
wake angle carefully. In addition, lift and drag coefficients can be extracted
from the numerical data and compared with the theory. Useful additional
simulations would include establishing the minimum free-stream Mach number
for a given deflection angle to obtain an attached shock at the leading edge
(i.e. to first find a detached shock). Alternatively, find the required opening
angle & (see figure 1) for a given Mach number to observe a detached shock.
The underlying theories, first introduced either in AERO306 Aerodynamics or
MECH326 Engineering Fluid Mechanics, have been revised in lecture 5.