Boundary-Layer-Transition Measurements in Full-Scale Flight Page: 4 of 12
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2 NACA RM H58E28
SYMBOLS
F Reynolds number per foot, V,/v, per ft
V, free-stream velocity, ft/sec
v kinematic viscosity
Rx nondimensional Reynolds number based on x
x distance from leading edge
A sweep angle
a angle of attack
hp altitude
M Mach number
T thickness, in.
INSTRUMENTATION AND TECHNIQUES
A fighter airplane was instrumented, as shown in figure 1, for
transition investigations on the wings. The basic wing has a modified
biconvex airfoil with a thickness ratio of 3.4 percent, a sharp leading
edge, and a slight amount of sweep (about 270). A 1/10-inch-thick
Fiberglas glove was installed on the right wing and was instrumented
with one row of transition detectors on both the top and bottom surfaces.
These detectors provided continuous monitoring of the laminar and tur-
bulent boundary-layer-flow conditions (ref. 1).
Chemical sublimation was employed for boundary-layer-flow visualiza-
tion on both wings, and cameras (fig. 1) were installed for recording the
chemical indications. Many investigators have used the chemical sublima-
tion technique in both wind tunnels and in flight (refs. 2, 3, and others).
These tests have extended the use of this technique in flight to speeds
near a Mach number of 2.0.
The transition-detector signals (see fig. 2) were multiplexed and
recorded on an oscillograph. The sequencing was scheduled to conform to
the locations of the detectors on the wing. This arrangement allowed
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Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr. Boundary-Layer-Transition Measurements in Full-Scale Flight, report, July 28, 1958; (https://digital.library.unt.edu/ark:/67531/metadc53370/m1/4/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.