High-speed wind-tunnel investigation of the effects of compressibility on a pitot-static tube Page: 3 of 24
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NACA RM No. A7.T1
references i and 2. Each pitot-static tube was tested at zero
pitch and zero yaw; one pitot-static tube of reference 2 was also
tested at small angles of pitch.
To supplement the existing information on this subject, the
present investigation was undertaken in the Ames 1- by 3-1/2-foot
high-speed wind tunnel to evaluate the effects of compressibility
on the velocity indications of a high-speed-type service pitot-
static tube at speeds up to approximatel 0.925 Mach number. The
tests were extended to include several small angles of pitch and
yaw.
SYMBOLS
The following symbols are used in this report:
p free-stream static pressure
pT static pressure given by pitot-static tube
q free-stream dynamic pressure. (.pV2)
M free-stream Mach number
compressibility factor 1 + -.+ -0- + --- ..~.
H free-tream total pressure '[p + i1 +Og ]
HT total pressure given by pitot-etatic tube
9 angle of-pitch
Single of yaw
p arc tan (s/)
O angle of inclination to free stream (approx. 12 + 2
for small angles)
- ---- - error.'in static press sure
H.-..
E - HT
error in total pressure
H-p2
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Stivers, Louis S., Jr. & Adams, Charles N., Jr. High-speed wind-tunnel investigation of the effects of compressibility on a pitot-static tube, report, August 4, 1947; (https://digital.library.unt.edu/ark:/67531/metadc58045/m1/3/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.