Accession Number:

AD0772687

Title:

Heat-Transfer Tests of Two Space Shuttle Orbiter Configurations at Mach Number 8

Descriptive Note:

Final rept. 25 Aug-28 Sep 1972

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1974-01-01

Pagination or Media Count:

45.0

Abstract:

Heat transfer tests were conducted on two Space Shuttle configurations at Mach number 8 to investigate the effects of nose geometry on windward and leeward heating and boundary layer transition. Free-stream Reynolds number based on model length was varied from 1.5 to 7.5 million at angles of attack from 20 to 50 deg. Windward centerline heating rates were in general agreement with calculated values except for laminar rates dowstream of the wing body junction. Differences in the location of the beginning of transition and the length of the transition zone were observed for the two configurations, but it was not clear whether variation in nose shape per se or the abrupt cross- sectional change from the nose to the aft fuselage and wing was the controlling factor.

Subject Categories:

  • Spacecraft Trajectories and Reentry
  • Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE