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delta wing has two attractors at 34.5 deg and -31 deg.32 The usual zero attractor
is not observed for the 60-deg delta wing at cy = 30 deg. The asymmetry in
numerical values of the attractors for the 60-deg delta wing is attributed to the
slight asymmetry in the free-to-roll model as stated elsewhere.32 The variation of
STABILITY AND CONTROL PROBLEMS AT HIGH ANGLES OF ATTACK 711
a)
c)
b)
d)
Fig. 8.41a Free-to-roll time histories of 60-deg dejta wing.32 (Courtesy ICAS.)
┏━━━━┳━┳━━━━┳━━━━━━━━━┓
┃\ ┃ ┃ ┃l- .r,~-t *.,t ┃
┣━┳━━┫ ┃ ┣━━━┳━━┳━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃ ┣━━╋━╋━━━━╋━━━╋━━╋━━┫
┃ ┃ ┃ ┃ ┃ ┃ - ┃ ┃
┃ ┣━━╋━╋━━━━╋━━━╋━━╋━━┫
┃ ┃ ┃ ┃ ┃r-_ ┃ ┃ - ┃
┃~ ┃\- ┃~ ┃7 ┃ ┃ ┃ ┃
┣━┻━━┻━╋━━━━╋━━━╋━━╋━━┫
┃ ┃:) ~(o ┃1- 59 ┃ ┃ ┃
┗━━━━━━┻━━━━┻━━━┻━━┻━━┛
po 0.. 02 t , 0.4 0~ 0,6
tme. s
Fig. 8.41b Free-to-roll time histories of 65-deg delta wing.33 (Courtesy AGARD.)
50
N
30
-
.: 20
=
:
10
o
N
-
: 20
=
-
~
o
-20
712 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
E
┏━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┓
┃Unstabte ┃
┃ ing . ┃
┃ ┃
┣━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┫
┃<S,ab,,o~ Cr ossing ,,,~ ~- d ┃
┗━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┛
Fig. 8.42 Schematic variation of rolling moment of65-deg delta wing at 30-deg angle
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