Effect of thrust per element on combustion stability characteristics of hydrogen oxygen rocket engines
Coaxial injector thrust effects on combustion stability of hydrogen-oxygen rocket engine
Hannum, N. P.↗
Engineering topics
Salmi, R. J.
Publications and source records attributed to Salmi, R. J..
Scale 1/14.2 investigation of submerged nozzle for SL-3 260-inch solid rocket
Submerged nozzle design for SL-3 260-inch solid propellant rocket engines
Pelouch, J. J., Jr.↗
Investigation of a submerged nozzle on a 1/14.2-scale model of the 260-inch solid rocket
Flow characteristics about submerged rocket nozzle model immersed in simulated exhaust gas
SUBMERGED BODY↗
Investigation of a submerged nozzle for solid rockets
Scale model compressed air tests of 260-inch solid rocket with submerged nozzle to determine exhaust flow velocity and direction in annular channel
ANNULAR FLOW↗
Investigation of a submerged nozzle for solid rockets.
Submerged nozzle for solid rockets, noting exhaust flow velocity and direction determination
EXHAUST VELOCITY↗
Compressed-air model investigation of solid rocket overpressures due to interference from aft-end ignition rocket
Solid rocket combustion chamber overpressures due to interference from aft-end ignition rocket
ROCKET BOOSTER↗
Experimental evaluation of various nonmetallic ablative materials as nozzle sections of hydrogen-oxygen rocket engine
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle sections
ROCKET NOZZLE↗
Performance of a mach 3.0 external-internal- compression axisymmetric inlet at mach numbers from 2.0 to 3.5
External-internal-compression axisymmetric inlet performance at supersonic speeds
INTERNAL COMPRESSION INLET↗
Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5
The effect of an external boundary layer on the performance of an axisymmetric external-internal-compression inlet was evaluated at Mach numbers of 3.0 and 2.5 and Reynolds numbers from 2.2 to 0.5 x 10(exp 6) per foot. The inlet was tested at locations up to two-thirds of the way into the 1.7- and 9.0-inch boundary layers generated by a flat plate and the tunnel floor, respectively. The inlet could be readily started at all conditions tested, including those where the boundary layer was separated upstream of the inlet by the various shock systems during the restart cycle. Although the inlet performance decreased with increasing immersion into the boundary layer at both Mach numbers, the inlet was more sensitive to boundary-layer ingestion at the design Mach number of 3.0.
Samanich, N. E.↗