
Accession Number : AD0612173
Title : TRANSIENT AIRLOADS ON A BODY OF REVOLUTION DUE TO INDICIAL SINKING AT A LARGE ANGLE OF ATTACK,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
Personal Author(s) : Ruetenik,J. Ray ; Brooks,W. Bryan
Report Date : AUG 1964
Pagination or Media Count : 44
Abstract : A nonlinear method is proposed for predicting the airloads on a slender, pointed body of revolution due to indicial sinking at a large angle of attack at supersonic or low hypersonic speeds. The method is an extension of Miles (NAVORD 2052) linearized theory for a slender, pointed body achieved by incorporating the Bryson theory of the indicial drag of a circular cylinder for the transient crossflow drag on the body. Comparisons of the steadystate theory are made with windtunnel data to indicate the range of Mach number, angle of attack, and fineness ratio over which the method could be expected to be applicable. It is found that the method is most useful for predicting the airloads on the cylindrical portion of the body, where vortices have the largest effect on the flow. (Author)
Descriptors : (*BODIES OF REVOLUTION, AERODYNAMIC LOADING), (*AERODYNAMIC LOADING, MATHEMATICAL PREDICTION), SLENDER BODIES, CYLINDRICAL BODIES, ANGLE OF ATTACK, VORTICES, DOWNWASH, SUPERSONIC FLIGHT, HYPERSONIC FLIGHT, DRAG, WINGS, WIND TUNNELS, GRAPHICS
Distribution Statement : APPROVED FOR PUBLIC RELEASE