Aerodynamic effect of volume addition to a high L/D wing/body at Mach 6.0.
Aerodynamic effect of volume addition to high lift to drag wing-body ratio at Mach 6
SLENDER BODY↗
Engineering topics
Ashby, G. C., Jr.
Publications and source records attributed to Ashby, G. C., Jr..
A parametric study of the aerodynamic charac- teristics of nose-cylinder-flare bodies at a mach number of 6.0
Longitudinal aerodynamic characteristics of nose cylinder-flare reentry bodies measured in hypersonic wind tunnel
LONGITUDINAL STABILITY↗
CENTER-LINE PRESSURE DISTRIBUTIONS ON TWO-DIMENSIONAL BODIES WITH LEADING-EDGE ANGLES GREATER THAN THAT FOR SHOCK DETACHMENT AT MACH NUMBER 6 AND ANGLES OF ATTACK UP TO 25 DEG
Center-line pressure distribution on two- dimensional bodies
PRESSURE DISTRIBUTION↗