Collection of zero-lift drag data on bodies of revolution from free-flight investigations Page: 3 of 374
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NACA TN 4201
p free-stream density
U free-stream velocity
M free-stream Mach number
CD drag coefficient based on body frontal area, Drag
Pressure - Free-stream pressure
Cp pressure coefficient,
Cf friction drag coefficient based on wetted area
r' = r/R where R is maximum body radius
x' = X/Znose or x/Zafterbody
rb' = rbase/R
Most data of this report were obtained by the following procedure:
A fin-stabilized model flying at or near zero lift was tracked with a
CW Doppler radar unit as it decelerated through a speed range from
supersonic Mach numbers to high subsonic Mach numbers. The resulting
velocity time history was arithmetically differentiated to give a decele-
ration time history. Shortly before or after the flight, a record of
the atmospheric properties (density, temperature, and wind velocity) was
obtained from the flight of a radiosonde balloon. This record, together
with a space-position time record of the flight, permitted the zero-lift
drag coefficient to be calculated. The tests differ only in the method
of launching the models into free flight and in the method of obtaining
the altitude time history.
Rocket Model Tests
The rocket-test method is the propulsion of the models by rockets
located in the model, or behind the model in the form of booster rockets
which dropped away after burnout. In these tests the models were also
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Stoney, William E., Jr. Collection of zero-lift drag data on bodies of revolution from free-flight investigations, report, September 3, 1957; (https://digital.library.unt.edu/ark:/67531/metadc56974/m1/3/: accessed April 19, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.