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AE-435

PROPULSION SYSTEMS-2

Project 2

Submitted by: Saim alar Kurtcebe (1679851)

Yeliz Yldz (182006)

Submitted t!: "r# $uz %z!l

Submi&&i!' date: 08122015

Contents

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Introduction............................................................................................................2

Part A...................................................................................................................... 2

The graph of angle of attack versus mach number at 40000 feet......................4

Part B...................................................................................................................... 4

The graph of angle of attack versus mach number b! decreasing altitude".. ....#

Part C...................................................................................................................... #

solutions.............................................................................................................. #

Conclusion..............................................................................................................$

Introduction' t*i& +r!,ect -e are .i/e' a de&i.' c!'diti!'# *e' -e are &u++!&ed t! !b&er/e t*e eect i'

a'.le ! attac i' 1&t &ta.e r!t!r ! c!m+re&&!r !r /ari!u& di&turba'ce# $ur mi&&i!' -a& t!

i'd i t*e c!m+re&&!r .!e& t! &tall !r t*e&e di&turba'ce# di&turba'ce !ccur& i' t*e

c!m+re&&!r t*e' -*at i'd ! e'.i'eeri'. &!luti!' &*!uld t! tae +lace t! rec!/er t*e

c!m+re&&!r r!m &tall c!'diti!' a& &tall i' c!m+re&&!r i& a &eri!u& act# c!m+re&&!r &tall&

a'd -e ca'3t rec!/er i'&ta'tly t*e' it may e/e' dama.e t*e e'tire e'.i'e#

Part A

4!r a .i/e' mac* 'umber (2) a'd .i/e' altitude (0#000 t) t*e &tatic tem+erature ! air

be!re c!m+re&&!r i'let -a& !btai'ed a& 69#70 (216#65 K) r!m a -eb&ite !

*tt+:---#e'.i'eeri'.t!!lb!#c!m&ta'dardatm!&+*ered60#*tml# *e' t*e t!tal

tem+erature at t*i& c!'diti!' -a& calculated by deri/ed r!m t*e ir&t la- !

t*erm!dy'amic& :

T0

T

=1+12

M2, (=1.4 forair)

'd &i'ce t*e t!tal tem+erature d!e& '!t c*a'.e r!m i'let .uide /a'e&(;&) t! r!t!r i'itial

+!i't (t*ere i& '! *eat tra'&er) acc!rdi'. t! t*e&e c!'&ta't t!tal tem+erature /alue& t*e &tatic

tem+erature /alue& !r t*i& ra'.e ( TS1 -a& !btai'ed by u&i'. ab!/e deri/ati!'#

*e ab&!lute /el!city ! blade !r t*i& ra'.e -a& calculated by u&i'. t*at relati!':

V1=Ma=M(RTS1) (=1.4,R=287J

kgK for air)

(

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*e't*e rati!'al /el!city ! blade -a& calculated by u&i'. t*at relati!':

u= r=( 20000rpm60s )(0.5m2)=1047.197551(m

s)

*e' by u&i'. /el!city tria'.le t*e relati/e /el!city /alue& ! blade (

1

-a& calculated

r!m .e!metry:

!r ab!/e +icture (

1=30 =0.523598775 rad

*e' by u&i'. t*i& /el!city tria'.le t*e relati/e l!- a'.le /alue& (

1

-a& al&!calculated#

1=arctan(u

V1

2

Vz1) Vz1=V1cos (1)

4i'ally t*e a'.le ! attac /alue& -a& calculated r!m:

AOA=1 ,(is sagg!ra"g#!$%i&%$as ak!" 74 )

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The graph of angle of attack versus mach number at 40000 feet

Part B

4!r t*i& +art t*e altitude a'd t*e /el!city ! air+la'e are b!t* c*a'.i'.# >e &tart r!m 0000

eet altitude a'd decrea&e t*e altitude -it* 5000 eet &te+&ize& a'd al&! decrea&e t*e mac*

'umber li'early a'd !btai' t*e data i' e/ery &te+&ize a& &ee' r!m t*e bel!- c*art#

ltitude(eet) &tatic(K)

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The graph of angle of attack versus mach number b! decreasing

altitude"

*e&e calculati!'& are eecuted i' e &imulated t*i& c!'diti!' -it* u&i'.

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Conclusion' t*i& +r!,ect t i& !b&er/ed t*e eect ! mac* a'd altitude !' c!m+re&&!r blade*u& a'y

u'c!'diti!'ed &ituati!' &uc* a& &tall i' c!m+re&&!r blade& a'd D(mi'u&) a'.le ! attac

!b&er/ed a'd &!l/ed e'.i'eeri'. +r!ce&

Reference List

*tt+:---#e'.i'eeri'.t!!lb!#c!m&ta'dardatm!&+*ered60#*tml

lecture '!te&

Matla !o"es#

clear

stragger=74;%stragger angleIGV=30;%IGVs angler=0.5;%mean radiusrpm=20000;%engine rpmR=287.058;%gas constantgam=.4;%gamagam!!2=0.2;%"gama#$2step=00;&!static=2'8; %(el)in

*ac+=linspace"2,0.',step$;%airplane mac+*ac+2=0.5;%mac+ at compressor inletu="rpm'0$-r-2-pi;orm=/step&!total"m$=&!static-"*ac+"m$12-gam!!2$;&!static2"m$=&!total"m$"gam!!2-*ac+212$;Velocit"m$=*ac+2-"gam-R-&!static2"m$$10.5;V!"m$=Velocit"m$-cosd"IGV$;V!"m$=Velocit"m$-sind"IGV$;!"m$=u#V!"m$;6eta"m$=atan"!"m$V!"m$$pi-80;

aoa"m$=6eta"m$#stragger;end

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