Accession Number:

ADB270502

Title:

Experimental Investigation of Rocket-Engine Ablative-Material Performance After Postrun Cooling at Altitude Pressures

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER

Personal Author(s):

Report Date:

1963-06-01

Pagination or Media Count:

35.0

Abstract:

An investigation was made to determine the effects of postrun cooling at simulated altitude pressures on ablative-rocket- material ablating characteristics. Two identical ablative nozzles were test fired six times each 40-sec tests on the end of a 150-pound-thrust hydrogen-oxygen rocket engine at an absolute chamber pressure of 100 pounds per square inch. One nozzle cooled after each test in an ambient-pressure environment the other nozzle cooled after each test while subjected to low-pressure vacuum conditions. The results are expressed in terms of nozzle weight 1055, char-layer thickness, and internal-dimension changes. Under the conditions of these tests, little noticeable effect occurred on the rates at which ablation materials erode either at sea-level pressures or at low pressures. in about 4 minutes of running, the throat area of each nozzle had essentially doubled, and the char was about 14 inch thick.

Subject Categories:

  • Miscellaneous Materials
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE