k		a0/2pi (usually assumed to be 1)
dsigdbeta	dSigma/dBeta
etaht		htail efficiency
etavt		vtail efficiency

M		flight Mach number
CL		lift coefficient
wingtotail	distance from LE wing root to LE htail root
wingtovtail	distance from LE wing root to LE vtail root

b		wing span
S		wing area
Lambda0		wing LE sweep (deg)
cr		wing root chord
ct		wing tip chord
hnw		wing neutral point

bht		htail span
Sht		htail area
Lambda0ht	htail LE sweep (deg)
crht		htail root chord
ctht		htail tip chord
hnht		htail neutral point

bvt		vtail span
Svt		vtail area
Lambda0vt	vtail LE sweep (deg)
crvt		vtail root chord
ctvt		vtail tip chord
hnvt		vtail neutral point

Ss		fuselage projected side area
Lf		fuselage overall length
d		cg distance from nose
h		fuselage average height
h1		fuselage height at 0.25*Lf
h2		fuselage height at 0.75*Lf
w1		fuselage width at 0.25*Lf
w2		fuselage width at 0.75*Lf