Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees Page: 4 of 20
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NACA RM H55E20a
M Mach number
n airplane normal acceleration, g units
q dynamic pressure, 4p2, lb/sq ft
S area of wing bounded by leading edge and trailing edge
extended to airplane line of symmetry disregarding
fillets, 2 c dy, sq ft
St area of horizontal tail, sq ft
V free-stream velocity, ft/sec
W airplane gross weight, lb
y lateral distance, ft
i indicated airplane angle of attack, deg
.be elevator position, deg
e pitching velocity, (positive nose up), radians/sec
pitching angular acceleration, radians/sec2
p mass density of air, slugs/cu ft
The Bell X-5 research airplane incorporates a wing which is variable
in flight between sweep angles of about 200 and about 58.70. A photo-
graph of the airplane in the 58.70 sweep configuration utilized in this
investigation is shown in figure 1. A three-view drawing of the airplane
is presented in figure 2. The airplane physical characteristics in the
58.7 sweptback configuration are given in table I.
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Reed, Robert D. Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees, report, July 21, 1955; (digital.library.unt.edu/ark:/67531/metadc61497/m1/4/: accessed August 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.