Download - NASA
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m 6_<br />
(,)<br />
7 m<br />
"o i..<br />
m 5--<br />
Q.<br />
X<br />
><br />
_ 4<br />
E<br />
e_ 3<br />
C<br />
_E 2<br />
O in<br />
"D C<br />
x<br />
g<br />
C<br />
E<br />
(a)<br />
Airspeed,<br />
KTAS<br />
• 200<br />
• 225<br />
o 250<br />
[] 275<br />
& 300<br />
o 325<br />
v 350<br />
0 _'<br />
-1.2 -1 -.8<br />
7 m<br />
6_<br />
5<br />
4<br />
3<br />
2<br />
1<br />
(b)<br />
0<br />
-1.2<br />
Airspeed,<br />
KTAS<br />
• 200<br />
• 225<br />
o 250<br />
[] 275<br />
A 300<br />
o 325<br />
v 350<br />
-1<br />
f<br />
e1+1<br />
_ 61-1<br />
130/_E/_S<br />
_2 / _ _G<br />
V O A r"l _ I LII= _ _<br />
.6 -.4 -.2<br />
Real part, per rev (expanded scale)<br />
w v 1=r-1_._<br />
01+1<br />
00 1 90 1 WE I US<br />
_ _1+1<br />
133/P0I<br />
_I<br />
_l%e' p3 + i<br />
Oo<br />
01 -1<br />
132/ vl 13G<br />
1<br />
U<br />
t._<br />
O0 / _0 / FI<br />
t<br />
4_ :)•_, 131 + 1<br />
0<br />
__.<br />
V O, A m _ IA i,<br />
-.8 -.6 -,4 -.2 0 .2<br />
Real part, per rev (expanded scale)<br />
Figure 15. Eigenvalues for corrected model with 1 o sweep, standard tips, and stiffness matrices for shimmed control<br />
system; 200-350 KTAS speed variation at 80% rotor speed. (a) Symmetric modes. (b) Antisymmetric modes.<br />
54<br />
.2
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