This paper deals with experimental investigation on cone-cylinder bodies having elliptical cross section of varying eUipticity ratio (ratio of semi-major axis to semi-minor axis) at supersonic Mach number. Seven bodies of cone-cylinder combination have been considered having the same nose and body fineness ratio but different eUipticity ratio. The nose and body fineness ratios of all bodies are 3.0 and 5.0 respectively. The eUipticity ratio of these bodies are 0.333, 0.500, 0.666, 1.0, 1.5, 2.0 and 3.0. Wind tunnel tests have been conducted on these bodies to obtain force and moment data at Mach number = 2.0. Based on experimental investigation, the effect of changing the eUipticity ratio on aerodynamic characteristics are presented. The present investigation has also resulted in augmentation of existing data base. The aerodynamic characteristics on these bodies have also been computed using an Euler code and compared with present experimental data.

Experimental aerodynamic characteristics of elliptical bodies with variation in elldpticity ratio

This paper deals with an experimental investigation of a family of cone-cylinder bodies having circular and equivalent elliptical (a/b = 2.0) cross sections with variation in nose and afterbody fineness ratios at Mach number 2.0. All elliptical bodies are tested at roll orientations of 0 deg (semimajor axis normal to cross flow velocity) and 90 deg (semiminor axis normal to crossflow velocity). The nose fineness ratios for these bodies are 1.0, 2.0, and 3.0, and the afterbody fineness ratios are 5.0 and 7.0. The effect of changing the cross section shape from circular to elliptical, the roll orientation, and the variation in nose and afterbody fineness ratios on aerodynamic characteristics are discussed. (Author)

MA Ramaswamy

Papers

Experimental investigation on cone cylinder bodies of elliptical and circular cross sections at M = 2.0