Inlet Geometry and Equivalence Ratio Effects on Combustion in a Ducted Rocket

Experimental Investigation of a Solid Propellant Ducted Rocket with a Chin Type Inlet

“…[1][2][3][4][5] Combustion performance is a critical issue in the efficient operation of SPDRs 1) because it directly affects mission performance. In the past few decades, many studies focused on the combustion performance of SPDRs, accounting for propellant type, [6][7][8][9] gas injection device, 7,[10][11][12][13] inlet type 10,[14][15][16][17] and chamber configuration. [18][19][20][21][22] However, most of these studies are forced on SPDRs with four inlets or two inlets, combustion characteristics of SPDRs with chin inlets are not found in open literature.…”

Experimental investigation of the effect of the air inlet angle and the combustion pressure in a ducted rocket combustor

“…Kim and Natan [14] conducted connected-pipe combustion experiments and a numerical analysis of the internal reacting §ow in a ducted rocket combustor at various equivalence ratios with an emphasis on the air inlet geometry e¨ect. They used three kinds of combustors in order to evaluate the air inlet geometry e¨ect; a two-inlet combustor with inlet angle of 90 • , a two-inlet combustor with inlet angle of 180 • , and a four-inlet combustor with inlet angle of 90 • .…”

“…The scope of the present study is to evaluate the energetic performance of a ducted rocket combustor operating at di¨erent conditions, using a connectedpipe testing setup at the Rocket Propulsion Center at the Faculty of Aerospace Engineering of the Technion-IIT. The experimental setup is based on the work of Kim and Natan [14].…”