8/17/2019 Adp Final Aravind
1/38
DESIGN OF 100 SEATER PASSENGER
AIRCRAFT
8/17/2019 Adp Final Aravind
2/38
REASON FOR CHOOSING
AROUND 46% OF INDIA’S ULTRA HIGH-NET-WORTH INDIVIDUALS LIVE INSMALL CITIES, MOST OF WHICH ARE STARVED FOR FLIGHT OPTIONS.
BUT RUNNING DAILY AIRBUS A32 OR BOEING !3! FLIGHTS TO AND FROM THESE CITIES IS NOT PROFITTABLE PROPOSITION.
T"# $&'#& ()*+# D&. A. P. . A/+01 1' ") 11#+ $& +#5#1('# $ )##& 7# *&&$ * "# 0&8. I $0* &9*:#+ /8 HAL
8/17/2019 Adp Final Aravind
3/38
INTERESTINGLY, INDIA;S TRANSPORT AIRCRAFT DREAM WAS INITIALLY CALLE
THE NATIONAL AEROSPACE LABORATORIES
8/17/2019 Adp Final Aravind
4/38
8/17/2019 Adp Final Aravind
5/38
MISSION PROFILE
8/17/2019 Adp Final Aravind
6/38
DESCRIPTION
Phase 1 : Engine start and warm up
Phase 2 : Taxiing
Phase 3 : Take !
Phase " : C#im$ t %ruise a#titude and a%%e#erate t %ruiseSpeed
Phase & : Cruise
Phase ' : (iter
Phase ) : Des%ent
Phase * : (anding
Phase + : Taxiing
Phase 1,: Engine shut dwn
8/17/2019 Adp Final Aravind
7/38
8/17/2019 Adp Final Aravind
8/38
A*&&$ +#)*9 /# /&# *"# '7& (")#)
CONCEPT-.( DESI/N:PRE(I0IN.R DESI/N:
DET.I( DESI/N:
8/17/2019 Adp Final Aravind
9/38
COLLECTION OF SIMILAR AIRCRAFTSDATA
8/17/2019 Adp Final Aravind
10/38
8/17/2019 Adp Final Aravind
11/38
PERFORMANCE GRAPH
6 ! !
2
3
4
6
!
&0*)# )(##+
8/17/2019 Adp Final Aravind
12/38
6 ! !
2
4
6
2
4&0*)# )(##+ VS )#)
&0*)# )(##+ '("
)#)
6 ! !
2
3
4
6
!&0*)# )(##+ '(" VS #*9" W
8/17/2019 Adp Final Aravind
13/38
6 ! !
2
2
3
3
4
&0*)# )(##+
8/17/2019 Adp Final Aravind
14/38
WEIGHT ESTIMATION
To estimate the following parameters of or !on!eptal "esign
Gross #ta$e %off weight &'T0(
Empt) weight &'0(
*ission fel weight &'F(
8/17/2019 Adp Final Aravind
15/38
Phase +,-. /oiter
8/17/2019 Adp Final Aravind
16/38
8/17/2019 Adp Final Aravind
17/38
10)*
&1,*1 kg
e2)*3+ kg
413)+2 kg
p+,,, kg
%"&, kg
Range",,, km
8/17/2019 Adp Final Aravind
18/38
AIRFOIL SELECTION
8/17/2019 Adp Final Aravind
19/38
8/17/2019 Adp Final Aravind
20/38
AIRFOIL SELECTION
NACA AIRFOIL FOR ROOT - 23
NACA AIRFOIL FOR TIP - 232
FROM SURVEY, RANGE FOR CL ' IS BETWEEN .2 TO .
CL '
8/17/2019 Adp Final Aravind
21/38
WING LOADINGJ K !4!.4!
8/17/2019 Adp Final Aravind
22/38
LANDING PERFORMANCE
8/17/2019 Adp Final Aravind
23/38
1+*9 +*)#
R V$ 2.29
R 4.6 '
"$ R
8/17/2019 Adp Final Aravind
24/38
S9 R S*
S9 2.4 '
FROM SURVEY, THE LANDING DISTANCE
3! '
S S S9 S$
S9 S- S- S$
GROUND ROLL DISTANCE
8/17/2019 Adp Final Aravind
25/38
WS &*
N
8/17/2019 Adp Final Aravind
26/38
TAE OFF PERFORMANCE
8/17/2019 Adp Final Aravind
27/38
T# +*)#
S9
0+234#&T#'(
FRO* S5R6E78 TA9E OFF DISTANCE
: 1400 m
R Sin ;
8/17/2019 Adp Final Aravind
28/38
R 3.2 '
5STALL
VSTALL !.43 ')
8/17/2019 Adp Final Aravind
29/38
C)- J-
8/17/2019 Adp Final Aravind
30/38
3.
8/17/2019 Adp Final Aravind
31/38
POWER RE?UIRED
POWER RE?UIRED PR T VQ
!6.4 W
.4 Q-.6
FROM SURVEY,
8/17/2019 Adp Final Aravind
32/38
EN/INE SE(ECTION
pratt5whittne6 P',,,T6pe: Tw sp# high $6passrati Tur$4an
(ength: 1,* in 829)" m
Diameter: &'9& in 819"" m
Dr6 weight: &,"' #$s 822*+ kg
Cmpnents
Cmpressr: sing#e stage 4an; " stage#w pressure %mpressr; ' stage highpressure %mpressr
Cm$ustrs: .nnu#ar
Tur$ine: sing#e stage high pressure
tur$ine; 3 stage #w pressure tur$inePer4rman%e
Thrust: 22;1,, < 2";,,, #$4 8++ < 12& kN
O=era## pressure rati: 2'91 < 2*92
>6pass rati: "9* < &9,
Thrust
8/17/2019 Adp Final Aravind
33/38
POWER LOADING
PA 624 W
POWER LOADING
8/17/2019 Adp Final Aravind
34/38
*9 )(#**
4D
W"#, CD
8/17/2019 Adp Final Aravind
35/38
CENTRE OF GRAVITY
CO0PONENTS EI/?T8kg
'@ $4 19+2 m 4 9
12@ $4 39*" m '* 1+*9 9#& % W 3!2. 9
2&@ $4 * m (81+ /8 4 9
3)@ $4 119*" m #+ #0*('# 4 % W 4.6 9
"&@ $4 1"9" m
$0)#19# #*9" '*
1+*9 9#&
3% W 6.! 9
',@ $4 1+92 m (81+ /8 2 4 9
+3@ $4 2+9)' m
"&*:1 5#&*1
)/*1*:#&
3 % W 6.! 9
8/17/2019 Adp Final Aravind
36/38
FRO* T
8/17/2019 Adp Final Aravind
37/38
SUMMARY OF THE REPORT
8/17/2019 Adp Final Aravind
38/38
In the pro!ess of estimating these performan!es parameters8 we ha?e fon" other
!hara!teristi!s of or airplane.
a2 Ta$eoff gross weight 'TO +1041 $g
=2 Fel weight 'f 1@3> $g
!2 Empt) weight 'e >@43 $g
"2 'ing loa"ing +@0 N#m>
e2 'ing areaS 312- m>
f2 *aimm lift !oeffi!ient 12@
g2 /#D ma 1+
h2 Aspe!t Ratio AR +2@>3
i2 TR,ma 11+ 9N &Tr=ofan engine(
2 Engine sele!te" &P' -000 (