PERFORMANCE OF A TURBOJET ENGINE IN COMBINATION WITH AN EXTERNAL-INTERNAL-COMPRESSION INLET TO MACH 2.88
Performance of turbojet in combination with external-internal-compression inlet at supersonic speed
COMPRESSION↗
Engineering topics
Bowditch, D. N.
Publications and source records attributed to Bowditch, D. N..
Dynamic response of a supersonic diffuser to bypass and spike oscillation
Investigation of amplitude and phase shift of static pressure variations in supersonic diffuser for separate oscillation of spike and bypass
PHASE SHIFT↗
Investigation of Inlet Control Parameters for an External-internal-compression Inlet from Mach 2.1 to 3.0
Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
POSITIONING EQUIPMENT↗
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50
Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7
ISENTROPIC PROCESS↗