A study of several parameters controlling the trajectories of a supersonic antiaircraft missile powered with solid- or liquid-fuel rockets Page: 4 of 43
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NACA RA No. 6G22 3
A theoretical analysis was carried out for the case of a missile
with zero drag fired vertically, and the results were compared with those
obtained from a step-by-step solution of the equations of motion for the
missile with normal drag.
COEFFICIENTS AND SYMBOLS
The following coefficients and symbols have been used in the pre-
sentation of the analysis and results:
I specific impulse of fuel, pounds per pound per second I K
X weight ratio of missile 1
j initial thrust ratio ()
CD drag coefficient (
D drag, pounds
SF frontal area, square feet
T thrust, pounds
V velocity, feet per second
Wo initial gross weight, pounds
W1 weight after fuel has burned, pounds
K rate of fuel consumption, pounds per second.
p air density, slugs per cubic foot
In addition, the following symbols have been used:
H altitude, feet
H1 altitude at end. of power flight, feet
I horizontal distance, feet
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Huntsberger, Ralph F. A study of several parameters controlling the trajectories of a supersonic antiaircraft missile powered with solid- or liquid-fuel rockets, report, April 24, 1947; (digital.library.unt.edu/ark:/67531/metadc57965/m1/4/: accessed December 16, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.