C.28 AIRCRAFT 24-SIAI MARCHETTI S211

694
Appendix C
Detailed Drawings for Different Aircraft
C.28
Aircraft 24--SIAI Marchetti S211
C.28 AIRCRAFT 24-SIAI MARCHETTI S211
Figure C-A23.4 Side CAD View of the Rockwell B-1 Aircraft
Table
C~A23.1
Aircraft
Dimension
A[ft]
b[ft]
bl{[ft]
bv[ft]
c[ftJ
c,[ft]
c,H[ft]
c,v[ft]
cr[ft]
crH[ft]
crv[ft]
rt[ft]
S[ff]
SfAVG[ft~]
SP-v[fr']
XHv[ft]
XwH,[ft]
Yv [ft]
ZH [ft]
ZH5 [ft]
Zw[ft]
Zwlf,[ft]
rH[deg]
rw [deg]
clf[deg]
sw[deg]
ALE[deg]
Au"[deg]
ALEv[deg]
Geometric Parameters for the Aerodynamic Modeling of the Rockwell B-1 Aircraft
B 1 (Extended wing)
Value
Bl (Swept Wing)
Value
89.4
137.7
44.8
17.9
13.0
17.5
16.6
129.2
78.2
44.8
17.9
22.1
31.9
. 16.6
28
28
7
5.4
7
5.4
7
1950
84.3
13.0
10.9
49.4
8.8
9.5
1521.6
84.3
22.1
10.9
43.3
8.8
9.5
12.8
1.8
11.3
12.8
1.8
11.3
0
-1
-1
2
16
41
57
2
67
41
57
0
Figure C-A24.1
3D View of the SIAl Marchetti S211 Aircraft
(Source: www.aviastar.org/index2.html)
Geometric Parameters and Typical Flight Conditions (see Appendix B, Aircraft 8)
Alt. = 25;00b.f( .Mach= 0.6
= 6iqri/~~6; 'h ,;198lbs/ft2 ,
c = 5,4ft, b = 26.3 ft
icc = 0.25, W = 4,000 lb
Vp,
s=
136 ft2 ,
"''
= o·
695
696
Appendix C
Detailed Drawings for Different Aircraft
G.28. Aireraft 24--SIAI Marchetti S21J
18.. 5"
13.1 ft
Fignre C-A24.2 General Dimensions of the SIAl S-211 Aircraft
Figure C-A24.4 Top CAD View of the SIAl S-21 I Aircraft
Fuselage Average
Cross-Sectional
Area =9.278 ff'
Figure C-A24.3 Front CAD View of the SIAl S-211 Aircraft
697
C.29
698
Appendix C
Aircraft 25-Supermarine Spitfire
Detailed Drawings for Different Aircraft
C.29 AIRCRAFT 25-SUPERMARINE SPITFIRE
Fuselage Side
Surface:
SBs = 116.009 Jf'
7,7
Average Fuselage
Heigllt:3.751t
23,2
Figure C-A24.5 Side CAD View of the SIAl S-211 Aircraft
Table C-A24.1
Geometric Parameters for the Aerodynamic Modeling of the SW S-211 Aircraft
Geometric Parameters
A[ft]
b[ft]
bH[ft)
bv[ft]
c[ft]
CAileron[ft]
CR[ft]
CWing(atAileron) [ft]
c,[ft]
c,H[ft]
Crv[ft]
CT[ft]
CTH[ft]
CTy[ft]
d[ft]
h[ft]
lcg[ft]
Y1 [ft)
S[ft2]
SB 5 [ft]
StAVG[tr]
Spv[fe]
Wmax[ft]
XAcR[ft]
8211 Aircraft
Geometric Parameters
18.4
26.3
13.3
5.8
XHV[ft]
SA
YA 0 [ft]
YR[[ft]
YRp[ft]
Yv [ft]
0.9
1.7
4.0
6.0
3.5
5.7
3.1
1.55
2.0
5
30.9
16.6
4.1
136
116.0
9.3
4.9
5.9
5.2
XwH,[ft]
X1[ft)
YA 1 [ft)
ZR 5 [ft]
Z1 [ft]
Z2[ft]
ZH [ft]
ZH5 [ft]
ZmaxJft]
Zw[ft]
ZwH,[ft]
rH[deg]
rw [deg)
EH[deg]
Ew[deg] (assumed)
ALE[deg]
ALEH[deg]
ALEy[deg]
8211 Aircraft
3.4
13.1
26.4
7.6
12.6
0.0
4.8
3.0
5.1
4.5
4.3
2.4
2.9
5.1
-1.1
1.3
0
-1.9
0
2
19.5
18.5
40
Figure C-A25.1 3D Vtew of the Supermarine Spitfire Aircraft
(Source: www.aviastar.org/index2.html)
Geometric Parameters and TypicafFiight Conditions
Alt.
= 33,000 ft, Mach = 0.35
s = .242 ft2 '
b -- 37 ft • Length = 30ft, Height
(estzmated) XcG = 0.25, W = 6,200 lbs
= 10ft
699