Performance comparison of three canard-type ram-jet missile configurations at Mach numbers from 1.5 to 2.0 Page: 4 of 32
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NAC RgEoF1"
CD0
CLCT-D
D
ACD
L2
f/a
h/RiCN
Co
c
Hdrag coefficient at zero lift
lift coefficient, L
qos
thrust - drag
coefficient of thrust minus drag rust- drag
drag
drag due to lift
fuel-air ratio
heating value of fuel, Btu/lb
scoop height
boundary layer scoop height parameter, cowl lip radius
mechanical equivalent of heat, 778 ft-lb/Btu
lift
Mach number
engine mass-flow ratio, unity when free-stream tube as defined by
cowl lip enters engine
total pressure
static pressure
dynamic pressure,
total wing plan-form area
missile velocity
fuel weight
fuel flow rate
missile gross weight
missile angle of attackJ
L
MP
p
S
V
Wf
wf
WG3
NACA RM E53Fll
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Fradenburgh, Evan A. & Kremzier, Emil J. Performance comparison of three canard-type ram-jet missile configurations at Mach numbers from 1.5 to 2.0, report, August 14, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59621/m1/4/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.