b = wing span, m (ft)
CD = airplane drag coefŽ cient
.CD/M D0:7 = airplane drag coefŽ cient at M D0:7
CDW = airplane wave-drag coefŽ cient
CL = airplane lift coefŽ cient
CM = airplane pitching-moment coefŽ cient
Cp = pressure coefŽ cient
c = chord,m (ft)
D = airplane drag, kgf (lbf)
h = maximum height of nacelle,m (ft)
L = airplane lift, kgf (lbf)
M = freestream Mach number
MDD = drag-divergenceMach number, Mach number
where d.CD /=dM D0:1
w = maximum width of nacelle,m (ft)
X = chordwise distance fromwing leading edge to
nacelle front face,m (ft)
x = chordwise distance from wing leading
edge, m (ft)
Y = spanwise distance from fuselage surface
to nacelle inboard surface,m (ft)
y = spanwise distance from fuselage centerline,m (ft)
Z = vertical distance from wing upper surface to
nacelle lower surface,m (ft)
´ = nondimensional span station, y=.b=2
