G.V. Bull

Aeroballistics range facilities as applied to aeronautical stability, performance and control studies and general aerophysics problems are reviewed briefly. This technique involves the use of guns to launch missile, aeroplane and other pertinent shapes at the desired Mach numbers. From observation of the models flight path, standard aeronautical stability derivatives can be determined by matching theoretically assumed forms of the equations of motion to the experimentally determined trajectory. From observation of the flow field about the body by standard techniques, such as shadowgraph and schlieren phot6graphy and interferometry, aerodynamic flow studies can be concluded. Experimental stability derivatives for cruciform wing-body and wing-body-tail configurations as determined from aeroballistics range tests are presented over a range of supersonic Mach numbers; these include roll damping, aileron power, pitching moment, center of pressure, normal force, pitch damping and drag derivatives. The application of the technique to aeroplane testing is discussed briefly and results from simple flight cases presented. Some basic aeronautical studies, in which pure wing planforms were tested, are reviewed and some test results summarized.

WGL-Tagung, Essen, 1957

Conference Paper

englisch

21,0 x 29,7 cm, 14 Seiten

Jahrbuch der Wissenschaftlichen Gesellschaft für Luftfahrt, 1957; S.247-260; 1958; Braunschweig : Vieweg

NA

Bestellbar

1958