Accession Number:

AD0840127

Title:

STEADY AND FLUCTUATING PRESSURES AROUND FLOW PROTUBERANCES ON THE MOL VEHICLE AT TRANSONIC SPEEDS

Descriptive Note:

Final rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1968-09-01

Pagination or Media Count:

46.0

Abstract:

A wind tunnel investigation was conducted in the Propulsion Wind Tunnel, Transonic 16T to obtain steady and fluctuating pressures to assess the aerodynamic effects on the local and downstream flow fields caused by large protuberances on the Manned Orbital Laboratory MOL vehicle. Pressure data were recorded at Mach numbers 0.80, 0.90, 1.10, 1.20, 1.40, and 1.55 for angles of attack of -7.5, 0, and 4 deg and angles of sideslip of -6 and 6 deg. Test results revealed that the left- and right-side auxiliary-equipment fairings and their afterbodies do not impose a significant interference effect on each other, whereas the horizon-sensor-fairing and auxiliary-equipment-fairing flow interaction attributes up to 50 percent of the pressure fluctuations at selected microphone locations. Of the four base configurations on the auxiliary-equipment fairings, the 10-deg conical afterbody exhibited the lowest overall dynamic- pressure level at all test conditions.

Subject Categories:

  • Spacecraft Trajectories and Reentry
  • Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE