Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration Page: 4 of 49
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NACA RM L57E31
Cm + Cm
static-stability derivative, dCm/d, per deg
yawing-moment coefficient about center of gravity
longitudinal damping derivatives, per radian
directional stability derivative, dCn/dp, per deg
diameter of jet at nozzle exit
moment of inertia in pitch about model center of gravity,
moment of inertia in yaw about model center of gravity,
fuselage length, ft
free-stream Mach number
Reynolds number based on wing mean aerodynamic chord
jet-exit static pressure, where n refers to motor number,
fuselage static pressure, lb/sq ft
wing static pressure, lb/sq ft
wing static pressure, where i refers to orifice number,
free-stream static pressure, lb/sq ft
period of short-period longitudinal oscillation, sec
1- - ---- -
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Judd, Joseph H. & Falanga, Ralph A. Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration, report, August 16, 1957; (digital.library.unt.edu/ark:/67531/metadc63486/m1/4/: accessed January 23, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.