Accession Number : AD0856410

Title :   Harmonic Oscillatory Motion of a Wing-Conic Fuselage System in a Supersonic Flow,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

Personal Author(s) : Carafoli, Elie ; Mateescu, Dan

Report Date : 15 JAN 1969

Pagination or Media Count : 18

Abstract : The paper is concerned with a study of supersonic, unsteady flows over a wing-conic fuselage system subjected to harmonic low-frequency oscillations. In this case, the motion of the wing-conic body system considered is composed of the following three motions: (1) harmonic oscillatory pitch about the Ox2-axis; (2) harmonic oscillatory translation along the Ox3-axis; and (3) harmonic oscillatory roll around the Ox1-axis, assuming that these oscillatory motions are of small amplitude and that the transverse dimensions of the fuselage are sufficiently reduced with respect to the Mach cone. This problem is reduced to the study of three supersonic steady conic flows, two of which are pure conic flows over a wing-conic body system, but the third is a second-order conic flow over the same system. The axial perturbation velocities for various positions of the leading edge of the wing with respect to the Mach cone were calculated, and an expression for the pressure coefficient in the cases of subsonic and supersonic leading edges was derived from these calculations. (Author)

Descriptors :   (*WING BODY CONFIGURATIONS, SUPERSONIC CHARACTERISTICS), CONICAL BODIES, FUSELAGES, OSCILLATION, LOW FREQUENCY, PITCH(MOTION), ROLL, LEADING EDGES, RUMANIA.

Subject Categories : Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE