Accession Number:

ADA024553

Title:

Heat-Transfer Tests on the Rockwell International Space Shuttle Orbiter with Boundary-Layer Trips (OH-54)

Descriptive Note:

Final rept. October 1974-Sep 1975

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1976-05-01

Pagination or Media Count:

43.0

Abstract:

Aerothermodynamic transition tests on a model of the forward half of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach Number 8. Phase-change paint was used to determine the aerodynamic heating rates on the windward side of Orbiter models during simulated atmospheric reentry. The majority of the data was obtained using spherical trip elements of varying sizes at three different axial stations along the model to determine the effect of roughness size and location on boundary- layer transition. Additional data were taken with models which had scale indentations that simulated external tank attachment rings, nose wheel well doors, and a surface insulation interface gap. Data were taken over an angle-of-attack range from 20 to 40 deg at free-stream Reynolds numbers, based on the total Orbiter scaled length, from 3.2 to 16.1 million. Typical heat-transfer data were presented to illustrate boundary-layer transition locations and sensitivities to test variables.

Subject Categories:

  • Unmanned Spacecraft
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE