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Results for “X-15 AIRCRAFT”

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 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
NASA NTRS1961

X-15 propulsion subsystem component development

The X-15 rocket-powered research aircraft was developed by the integrated effort of various areas such as aerodynamics, thermodynamics, and structures. The propulsion subsystem development at the onset of the program was handicapped for varied causes. As a result, early in the flight testing phase, many time-consuming and costly delays were encountered as a result of individual component failures. A review of the X-15 propulsion subsystem components is presented, with a discussion of some of the development problems, how they were alleviated, and how they may be reduced or avoided in future programs. In order to avoid these problems in the future, a program is recommended in the hope that it will increase component reliability commensurate with vehicle objectives.

Robert L. Wiswell↗
NASA NTRS1958

Centrifugal simulation of the X-15

Paper presents the results of physiological tolerance tests of the pilot to the oscillating accelerations of large amplitude and long duration which might occur as a result of aircraft heading errors during reentries from the altitude mission in the X-15 without control augmentation.

Clark, Carl↗
NASA NTRS1958

Effects of aerodynamic heating on X-15 temperatures

Paper describes examples which show how wind-tunnel model tests of the actual configuration of the aircraft aid in aerothermodynamic analyses and how these tests have made possible increased accuracy in structural temperature prediction. Also, from this and other research, development and design work on the X-15 has been done to accomplish a design consistent with the specified flight requirements. In this work, structural temperatures have been held within acceptable limits by providing sufficient heat sink material. Limited areas of the skin and leading edges are expected to attain temperatures greater than 1,200 degrees F. However, these areas have been carefully investigated for the effect of these higher temperatures on the structure and have been found to be satisfactory.

Kinsler, Martin R↗
NASA NTRS1958

Development of X-15 escape system

The content of this paper is concerned primarily with testing and determining the suitability of such factors as cockpit mobility, escape potential, mechanical reliability, post-separation performance, and airframe compatibility. Integrating the results of the various studies led to the conclusion that the pressure suit in combination with the open ejection seat would best satisfy the X-15 emergency-escape requirements by virtue of elimination of capsule-imposed penalties on aircraft performance and significant reduction in development time.

Hegenwald, J F↗
NASA NTRS1963

THE X-15 PROGRAM

X 15 flight tests showing structure, powerplant, and auxiliary systems problems, and emphasizing pilots boost, entry, and landing techniques

FLIGHT TEST↗