A Survey of Unsteady Hypersonic Flow Problems

Y
Y
yi
6
F
A
K
- 66 -
instantaneous angle of attack
amplitude of oscillatory angle of attack
mean angle of attack
4iFT
ratio of specific heats
flight path angle to local horizontal
Appendix III
flight path angle at start of re-entry
1
quantity specified by the largest of the thickness ratio, mean
incidence of body or surface, and the dimensionless amplitude
of the time-dependent motion - Appendix II
the thickness ratio of aerofoil section - Appendix IV
apparent boundary layer thickness - wall to 9% free-stream
velocity point (Figs. 64 and 65)
prefix denoting a small variation of a quantity in the variational
problem (Appendix IV)
semi-apex angle of delta wing
density ratio across shock wave
cc-ordinate axis (Fig. 6)
non-dimensional value of c (equation (2.23)) 3
= oh/wf (AppendFx IV)
co-ordinate axis (Fig. 6)
non-dimensional value of q (equation (2.23))
Appendix II
steady surface slope measured fran chordline or body axis
value of 8 at the nose
order of magnitude of perturbations
relative density of vehicle (equation (3.1))
mass ratio of wing
= m/4bap for tnc-dimensional sectionj m is mass per
unit span b = g/2
= &basp for a wingi m is mass of wing b = z/2
s = span of wing
local viscosity
viscosity of free stream