A Survey of Unsteady Hypersonic Flow Problems
A Survey of Unsteady Hypersonic Flow Problems
A Survey of Unsteady Hypersonic Flow Problems
Create successful ePaper yourself
Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.
h<br />
iB<br />
IB<br />
k<br />
X<br />
x crit<br />
x Y<br />
c<br />
c<br />
Lb<br />
Li'Li<br />
m<br />
m<br />
m<br />
m<br />
Y<br />
%<br />
%<br />
Idi’M!<br />
. I<br />
n<br />
%<br />
P<br />
&.a<br />
- 63 -<br />
displacement <strong>of</strong> section in plunge (flutter)<br />
non-dimensional form <strong>of</strong> I B :pSbs<br />
pitching moment <strong>of</strong> inertia <strong>of</strong> a body about its centre <strong>of</strong> gravity<br />
frequency parameter - I<br />
U<br />
convergence factor for pitching oscillations <strong>of</strong> a vehicle flying<br />
on a re-entry path defined by equation (3.12)<br />
critical value <strong>of</strong> X in equation (3.14)<br />
CL m<br />
-+-<br />
2 PSR<br />
pitching radius <strong>of</strong> gyration <strong>of</strong> B body about its oentre <strong>of</strong> gravity<br />
body length<br />
panel length - in flutter studies<br />
ratio <strong>of</strong> lift to drag<br />
see definitions <strong>of</strong> derivatives (i = 1 to 4)<br />
mass <strong>of</strong> vehicle - Appendix III<br />
mass per unit span <strong>of</strong> two-dimensional section<br />
mass <strong>of</strong> wing or cone<br />
mass/unit area Of panel<br />
free stream or flight Mach number U/s,<br />
flutter Mach number<br />
Mach number <strong>of</strong> boundary layer in approximate calculation <strong>of</strong><br />
boundary layer damping in Figs. 64 to 65.<br />
see definitions <strong>of</strong> derivatives (i = 1 to 4)<br />
I<br />
Appendix IV<br />
number <strong>of</strong> circumferential nodes in the flutter <strong>of</strong> a cylindrical<br />
shell<br />
mid-plane stress in panel (Fig. 63)<br />
local pressure .<br />
free-stream static pressure
Change language