Current status and opportunities for improved high-temperature materials for advanced turbojet engines.
High temperature nickel and cobalt superalloys for turbojet engines
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High temperature nickel and cobalt superalloys for turbojet engines
Solar spectrum measurement, discussing equipment design, testing and application
Design and testing of crack-notched specimens for determination of resistance of materials to unstable opening-mode crack extension under plane strain conditions
NASA program involving orbiting satellite studies of natural and cultural resources
Space radiation environment effects on spacecraft materials and components
Chemical studies of life origin, discussing chemical and biological evolution, precellular organization and synthesis of various life compounds
ICRPG liquid propellant thrust chamber performance evaluation methodology, reviewing imperfections and limitations
Scanning electron microscopy for reliability studies in semiconductor devices
Mathematical models of human vestibular system for dynamic space orientation, using control theory
Solar photoelectric power ion propelled probe of asteroid region, describing design and mission planning
Electric propulsion technology status for auxiliary and solar electric prime propulsion applications
Oxygen difluoride/diborane propellant thrust chamber and injector technology, discussing engine duty cycles and performance
This paper summarizes some of the techniques used in N.A.C.A. research programs, in flight and in tunnels, to solve aircraft icing problems and it indicates the scope of the data avail-able for the design of aircraft icing protection systems. Sufficient data have been obtained, generalized where possible, and techniques have been established whereby icing -protection requirements for most aircraft components can be determined sufficiently accurately for engineering purposes. The Appendices discuss the icing facilities at the N.A.C.A. Lewis laboratory in detail, specific test equipment and techniques used in conducting tests in icing wind tunnels, and several icing instruments.
The lifting body concept was originally conceived by the Ames Research Center, and the design was developed over a period of years, from 1957 to 1964. By using a cone as a basic entry shape and modifying it to obtain lift and control, the M-2 shape evolved. In a cooperative venture with the NASA Ames Research Center to determine if a pilot could maneuver, flare, and land this class of vehicle, the Flight Research Center constructed a lightweight version of the lifting body, the M2-F1 vehicle. This vehicle was constructed during the fall of 1962 and spring of 1963 and extensively flight tested during the summer of 1963. Because of the success of the M2-F1 flight program, the research program was extended to include vehicles that would be representative of mission weight and wing loading. Figure 1 shows the three vehicles in the present lifting body program. On the left is the X-24A vehicle, which evolved from the U. S. Air Force's SV-5 PRIME vehicle; in the center is the M2-F3 vehicle, which is a modified version of the M2-F2 vehicle; and on the right is the HL-10 vehicle, which evolved from work at the NASA Langley Research Center.
Theoretical and experimental calculations in analysis of optical spectra of uranium
Economical reusable space shuttle development for cargo and passenger transportation to and from orbit
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