ECOR 2606 Lab Test #1 v1
The diagram illustrates a gas flowing through a nozzle.
As the cross sectional area of the nozzle gets smaller
and smaller,
the gas flows faster and faster until, at the
choke point, it is flowing at Mach 1 (
M
= 1).
If the Mach number of the flow at some point in the
nozzle is known, the cross sectional area at that point
can be calculated using the following formula:
1
2
/
1
2
2
1
1
1
2
*
M
M
A
A
where
A
is the cross sectional area at the point of interest
M
is the Mach number of the flow at this point
A
* is the cross sectional area at the choke point
γ
is the specific heat ratio for the gas
Part I (3 marks):
Write a function mfile (area.m) that, given
M
,
A
*, and
γ
(gamma), computes and returns
A
. The
formula is only valid for 0 <
M
<= 1.
If
M
is outside of this range your function should generate
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 Winter '09
 Fluid Dynamics, Mach number, De Laval nozzle, cross sectional area

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