Page 128 - Aeronautical Engineer Data Book

104 Aeronautical Engineer’s Data Book

Taper ratio λ = C t /C R = 1.0 AR tanΛ LE
2.0
6
1.8
5
1.6
4
1.4
X a.c.
1.2
3
C r
1.0 2
0.8
1
0.6
0.4
Subsonic Supersonic
0.2
C t /C R = 0.5 AR tanΛ LE
1.4 6
Sonic T.E.
1.2 5
1.0 4
X a.c. 3
0.8
C r
2
0.6 1
Unswept T.E.
0.4
0.2
Subsonic Supersonic
0
C t /C R = 0.25 AR tanΛ LE
1.2
Sonic T.E.
1.0 6
5
X a.c. 0.8 4
3
C r
0.6 Unswept T.E. 2
1
0.4
0.2
Subsonic Supersonic
0
0 1 0 1 0
β β
tanΛ LE tanΛ LE
β tanΛ LE tanΛ LE β
Fig. 6.7 Wing aerodynamic centre location: subsonic/
supersonic flight. Originally published in The AIAA
Aerospace Engineers Design Guide, 4th Edition. Copyright
© 1998 by The American Institute of Aeronautics and
Astronautics Inc. Reprinted with permission.