Accession Number:

ADA034733

Title:

Simulated Thermal Protection Tile Roughness Effects on Windward Surface Heat Transfer on the Rockwell International Space Shuttle Orbiter

Descriptive Note:

Final rept. 14 Nov-10 Dec 1975

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1977-01-01

Pagination or Media Count:

62.0

Abstract:

Heat transfer tests on the forward half of the 0.04-scale models of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach number 8. Infrared scanning was used to determine the influence of simulated thermal protection tile roughness on windward surface heat transfer level and distribution. Tile roughness was in the form of tile surface mismatch and gaps between titles. Tile height measured from the smooth body wall ranged from -0.020 in. cavity to 0.025 in. protuberance, and gap width ranged from 0 to 0.020 in. Data were obtained at angles of attack of 30 to 40 deg at zero side-slip at free-stream Reynolds numbers from 2,200,000 to 15,100,000 based on the total Orbiter scaled length. The infrared system is described, and data are presented which illustrate the influence of the major test parameters.

Subject Categories:

  • Spacecraft Trajectories and Reentry
  • Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE