Effective thermal conductivities of four metal-ceramic composite coatings in hydrogen-oxygen rocket firings / by Ralph L. Schacht, Harold G. Price, Jr., and Richard J. Quentmeyer.

Format:

Book

Government document

Author/Creator:

Schacht, Ralph L., author.

Price, Harold G., author.

Quentmeyer, Richard J., author.

Contributor:

United States. National Aeronautics and Space Administration, issuing body.

Series:

NASA technical note ; D-7055.

NASA/TN ; D-7055

Language:

English

Subjects (All):

Coatings--Thermal properties--Testing.

Coatings.

Heat--Transmission.

Heat.

Composite materials--Effect of temperature on--Testing.

Composite materials.

Rockets (Aeronautics)--Nozzles.

Rockets (Aeronautics).

heat transmission.

Physical Description:

1 online resource (41 pages) : illustrations.

Place of Publication:

Washington, D.C. : National Aeronautics and Space Administration, November 1972.

Summary:

An experimental investigation was conducted to determine the effective conductivities of four plasma-arc-sprayed, metal-ceramic gradated coatings on hydrogen-oxygen thrust chambers. The effective thermal conductivities were not a function of pressure or oxidant-to-fuel ratio. The various materials that made up these composites do not seem to affect the thermal conductivity values as much as the differences in the thermal conductivities of the parent materials would lead one to expect. Contact resistance evolving from the spraying process seems to be the controlling factor. The thermal conductivities of all the composites tested fell in the range of 0.75 to 7.5 watts per meter kelvin.

Notes:

"November 1972."

Includes bibliographical references (page 18).

Description based on online resource, PDF version; title from title page (NASA, viewed on June 1, 2021)

Other Format:

Online version: Schacht, Ralph L. Effective thermal conductivities of four metal-ceramic composite coatings in hydrogen-oxygen rocket firings

OCLC:

23137432