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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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At least 253 records · Page 14
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

Comparisons of free-flight experimental and predicted heating rates for the Space Shuttle

Experimental windward-ray heating rates measured during entry of the first Space Shuttle Orbiter mission are compared with predicted rates based on engineering and detailed equilibrium-air analyses. The experimental heating rates were reduced from temperature-time histories which are available only for the trajectory period after blackout which corresponds to a freestream Mach number and altitude of approximately 11.0 and 53 km, respectively. The experimental heating rates are computed for two measured emissivity data sets. The differences in the experimental heating rates based on the two emissivity data sets are sufficiently large that different interpretations of the STS-1 aerothermal environment may be inferred.

Zoby, E. V.↗
NASA NTRS1988

A research study for the preliminary definition of an aerophysics free-flight laboratory facility

A renewed interest in hypervelocity vehicles requires an increase in the knowledge of aerodynamic phenomena. Tests conducted with ground-based facilities can be used both to better understand the physics of hypervelocity flight, and to calibrate and validate computer codes designed to predict vehicle performance in the hypervelocity environment. This research reviews the requirements for aerothermodynamic testing and discusses the ballistic range and its capabilities. Examples of the kinds of testing performed in typical high performance ballistic ranges are described. We draw heavily on experience obtained in the ballistics facilities at NASA Ames Research Center, Moffett Field, California. Prospects for improving the capabilities of the ballistic range by using advanced instrumentation are discussed. Finally, recent developments in gun technology and their application to extend the capability of the ballistic range are summarized.

Canning, Thomas N.↗
NASA NTRS1992

A method of analyzing holographic interferograms of ballistic models in hypersonic free-flight

The objective of this research was to develop a method to extract integrated flowfield density information from finite-fringe interferograms produced with a laser holographic interferometer. This method was applied to two sets of holograms. An aeroassist flight experiment model flown in a mixture of 50 percent air - 50 percent argon and a blunt slender cone flown in air were flown at Mach 14.5 into freestream static pressures of 0.04 and 0.08 atm, respectively. The method of analysis can be separated into two main divisions. The first step is to identify fringes inside the wake in terms of the fringes in the freestream. This is important because refraction effects have obscured the region near the shock such that fringes cannot be followed into the wake region. The second step is to extrapolate the freestream fringes into the wake to determine the location of disturbance-related fringe shifts. Coupled with assumptions about the shape of the wake region, the locations of the disturbance-related fringe shifts can be related to the integrated density.

Kieffer, Douglas L.↗