Thermodynamic calculation of turbojet engine with afterburner Givens: Flight conditions: M

$=$

$0$

;H

$=$

$0$

$$Required thrust: F

$=$

$100000$

N Main working process parameters:

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pi

$\_$

$($

$0$

c

$)$

$=$

$12$

;T

$\_$

$($

$03$

$)$

$=$

$1650$

K;T

$\_$

$($

$0$

aib

$)$

$=$

$2000$

K Coefficients and other givens:

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sigma

$\_$

$($

i

$)$

$=$

$0\mathrm{.}8$

;

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eta

$\_$

$($

comp

$)$

$=$

$0\mathrm{.}86$

;

$\backslash$

sigma

$\_$

$($

b

$)$

$=$

$0\mathrm{.}96$

;H

$\_$

$($

n

$)$

$=$

$42900$

k

$($

j

$)$

$/$

$($

k

$)$

g;

$\backslash$

eta

$\_$

$($

g

$)$

$=$

$0\mathrm{.}98$

;

$\backslash$

eta

$\_$

$($

T

$)$

$=$

$0\mathrm{.}9$

;

$\backslash$

eta

$\_$

$($

mach

$)$

$=$

$0\mathrm{.}99$

;g

$\_$

$($

othar

$)$

$=$

$0$

; k

$\_$

$($

g

$)$

$=$

$1\mathrm{.}3$

;R

$\_$

$($

g

$)$

$=$

$287\mathrm{.}6$

$($

J

$)$

$/$

$($

k

$)$

gK;

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sigma

$\_$

$($

$($

a

$)$

$/$

$($

b

$)$

$)$

$=$

$0\mathrm{.}94$

;

$\backslash$

eta

$\_$

$($

g

$($

a

$)$

$/$

$($

b

$)$

$)$

$=$

$0\mathrm{.}97$

;

$\backslash$

phi

$\_$

$($

n

$($

a

$)$

$/$

$($

b

$)$

$)$

$=$

$0\mathrm{.}98$

;k

$\_$

$($

g

$($

a

$)$

$/$

$($

b

$)$

$)$

$=$

$1\mathrm{.}25$

;R

$\_$

$($

g

$($

a

$)$

$/$

$($

b

$)$

$)$

$=$

$288$

$($

J

$)$

$/$

$($

k

$)$

gK k

$=$

$1\mathrm{.}4$

;R

$=$

$287$

$($

J

$)$

$/$

$($

k

$)$

gK Perform the following: Draw the schematic diagram of the given engine with appropriate station numbering and the corresponding thermodynamic cycle in p

$-$

v and T

$-$

S coordinate systems Calculate all the thermodynamic parameters at each station of the engine including the critical parameters of the jet nozzle

$($

$$that is to mean: total and static pressures, total and static temperatures, total compression ratio, jet nozzle pressure ratio, jet nozzle critical pressure ratio, jet nozzle critical temperature and pressure and other parameters that can be used as an input to determine engine main and working process parameters

$)$

$$Calculate F

$\_$

$($

sp

$)$

$,$

f

$\_$

$($

sp

$)$

$,$

m

$\_$

$($

a

$)$

$^$

$($

$$

$)$

$$and cross sectional area of the inlet section and the jet nozzle section Calculate the engine useful cyclic work, engine thermal, propulsive and overall efficiencies Use a standard format to submit your technical report