The effect of varying secondary Mach number and injection angle on secondary gaseous injection into a supersonic flow.
Koch, Larry Neil
Collins, Daniel J.
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This study was undertaken to investigate the effects of varying both the secondary Mach number and angle of inclination relative to the primary stream on the flow field generated by the interaction of a secondary jet with a supersonic mainstream. The experimental portions of this investigation were conducted at a primary Mach number of 2.80 in the Naval Postgraduate School Supersonic Wind Tunnel. Data are presented and compared with various theories. This presentation includes correlation of the penetration height of the secondary flow, bow-shock shape by non-dimensionalization with respect to various parameters and correlation of interaction side force amplification factor.
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