Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration Page: 3 of 39
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NACA RM L50J27
of an investigation of the stability and control characteristics of the
model in the landing configuration with dive brakes retracted and extended.
The results of exploratory tests made to determine the effect of leakage
through the fuselage at the wing root are also included.
SYMBOLSThe
positive
CL
CX
CyZ
Cm
Cn
X
Y
Z
L
M
N
S
c
C50
c'system of axes employed, together with an indication of the
forces, moments, and angles, is presented in figure 1.
lift coefficient (Lift/qS)
longitudinal-force coefficient (X/qS)
lateral-force coefficient (Y/qS)
rolling-moment coefficient (L/qSb)
pitching-moment coefficient (M/qSc50)
yawing-moment coefficient (N/qSb)
longitudinal force along X-axis, pounds
lateral force along Y-axis, pounds
force along Z-axis, pounds (Lift = -Z)
rolling moment about X-axis, foot-pounds
pitching moment about Y-axis, foot-pounds
yawing moment about Z-axis, foot-pounds
free-stream dynamic pressure, pounds per square foot (pV2/2)
wing area, square feet
wing mean aerodynamic chord (based on plan forms shown in
fig. 2), feet
mean aerodynamic chord at 500 sweep, feet
streamwise wing chord, feet
wing chord perpendicular to quarter-chord line of unswept wing,
feet
CONFIDENTIAL2
CONFIIENTIAL
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Becht, Robert E. Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration, report, December 18, 1950; (https://digital.library.unt.edu/ark:/67531/metadc58634/m1/3/: accessed April 18, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.