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Results for “rocket”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 1,495 records · Page 83

All sources NASA NTRS DOE OSTI

NASA NTRS1963

SCALE MODEL TESTING OF 90 DEG TURN EJECTOR SYSTEMS FOR ROCKET ENGINE ALTITUDE SIMULATION

Scale model testing of 90-deg turn ejector systems for rocket engine simulation

ROCKET ENGINE↗

NASA NTRS1963

RECENT PROGRESS IN DETONATION RESEARCH AND ITS RELATION TO ROCKET PROPULSION

Gaseous phase of detonation - relation to rocket propulsion

ROCKET ENGINE↗

NASA NTRS1963

FLOW PATTERNS IN A PHASE CHANGE ROCKET COMBUSTION MODEL

Hot kerosene flashing in vertical tube - simulation of flow pattern of phase-change rocket combustor

FLOW PATTERN↗

NASA NTRS1963

THEORETICAL AND EXPERIMENTAL MODELS FOR UNSTABLE ROCKET COMBUSTOR

Theoretical models and experimental rocket combustors for study of combustion process instability

COMBUSTION INSTABILITY↗

NASA NTRS1963

SCALING PROBLEMS ASSOCIATED WITH UNSTABLE BURNING IN SOLID PROPELLANT ROCKETS

Scaling in unstable combustion processes of solid propellant rocket engines

SOLID PROPELLANT ROCKET ENGINE↗

NASA NTRS1958

Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.

FREE FLIGHT↗

NASA NTRS1963