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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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Water-landing characteristics of a 1/10-scale model of a winged missile
Water landing characteristics of winged missile scale model
Experimental investigation of base heating and rocket hinge moments for a simulated missile through a Mach number range of 0.8 to 2.0
Jet-stream interaction effects on rocket engine studied with simulated ballistic missile using liquid oxygen and JP-4 fuel mixture
Craters produced by missile impacts
Impact craters produced by missiles with large kinetic energy
American Astronautical Society, Southeastern Symposium on Missiles and Aerospace Vehicles Sciences, Huntsville, Ala., December 5-7, 1966, Proceedings. Volume 1.
Missiles and aerospace vehicles sciences - AAS CONFERENCE, Huntsville, Alabama, December 1966, Volume 1
American Astronautical Society, Southeastern Symposium on Missiles and Aerospace Vehicles Sciences, Huntsville, Ala., December 5-7, 1966, Proceedings. Volume 2.
Missiles and aerospace vehicles sciences - Conference, Huntsville, Alabama, December 1966, Volume 2
Flight Investigation of a Roll-stabilized Missile Configuration at Varying Angles of Attack at Mach Numbers Between 0.8 and 1.79
A missile research model was flown at supersonic speed to determine the quality of automatic roll stabilization at varying angles of attack. Aerodynamic rolling and pitching derivatives were determined from the flight record. It was concluded that the combination of the gyro-actuated automatic pilot with wing-tip ailerons provided adequate roll stabilization under conditions encountered in flight.
Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 II : Presentation and Analysis of Force Measurements
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
ELECTRICAL SYSTEMS IN MISSILES AND SPACE VEHICLES
Missile and space vehicle electrical systems - space science
A SIMPLIFIED STATISTICAL MODEL FOR MISSILE LAUNCHING - 1
Launching pad operations for missiles - statistical probability and prelaunch problems
A data storage system for obtaining missile re- entry heating data.
Missile data storage system for obtaining reentry heating data, employing ferrite memory and digital and analog circuitry
Mathematical models of missile launching
Mathematical models of simultaneous countdown but nonsimultaneous missile launching program
Aerodynamic characteristics of a family of multistage missiles at a mach number of 6.0
Wind tunnel investigation of aerodynamic characteristics of cone-cylinder-flare multistage missile configurations at supersonic speed
A data storage system for obtaining missile reentry heating data
Miniature data storage system for missile reentry heat data
A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios. Four trajectories were chosen for detailed temperature computation from among those trajectories estimated to be possible. Temperature calculations were made for both "conventional" (for example, copper, Inconel, and stainless steel) and "unconventional" (for example, beryllium and graphite) materials. Results of the computations showed that an impact Mach number of 0.5 was readily obtainable for a body constructed from conventional materials. A substantial increase in subsonic impact velocity above a Mach number of 0.5 was possible without exceeding material temperature limits. A weight saving of up to 134 pounds out of 822 was possible with unconventional materials. This saving represents 78 percent of the structural weight. Supersonic impact would require construction of the body from unconventional materials but appeared to be well within the range of attainability.
Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a Mach number of 2.01
Lateral and longitudinal aerodynamic characteristics of hypersonic missile configurations with canard controls in supersonic pressure tunnel
An event recorder for obtaining missile heat- shield ablation data.
Event recorder for in-flight measurements of missile heat-shield ablation
Supersonic aerodynamic characteristics of a model of an air-to-ground missile
Supersonic aerodynamic characteristics of model of air-to-surface missile