An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds Page: 3 of 68
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NACA RM L56F18a
An investigation has been conducted in the Langley 8-foot transonic
tunnel to evaluate some of the effects of sting-support configuration on
the drag characteristics of a systematic series of afterbodies. The
tests were conducted at an angle of attack of 00 through the Mach number
range from 0.80 to 1.10 for stings with varying cone-angle, length, and
diameter. The sting effects determined are compared with data of jet
effects on the same afterbodies.
SYMBOLScross-sectional area
pressure drag coefficient, PAZ
increment between total afterbody pressure
at any given Db/l and at Db/ = 0
increment between total afterbody pressure
at Db/ = oo and at Db/t = 0drag coefficient
drag coefficientdiameter
ratio of jet total pressure to free-stream static pressure
body length
sting length between model base and sting cone
free-stream Mach number
P1 - P0
pressure coefficient,
qo
static pressure
dynamic pressure
Reynolds number based on body length
jet total temperature, OFCONFIDENTIAL
AcDmax
D
L
M
P
p
R
Tj2
CONFIDENTIAL
Hj/Po
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Cahn, Maurice S. An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds, report, September 24, 1956; (https://digital.library.unt.edu/ark:/67531/metadc65386/m1/3/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.