Body Flap Heat Transfer Data from Space Shuttle Orbiter Entry Flight Test Maneuvers.
Abstract
The Space Shuttle Orbiter has conducted various flight test maneuvers during the Orbital Flight Test Program and beyond in order to establish heating rates at various angles of attack and center of gravity positions. The objective of this project was to investigating the heating effects on the body flap during the entry flight test maneuvers and determine the limits on the flap deflections for an aft center of gravity envelope on the Orbiter. An analysis program available from the Air Force Flight Test Center AFFTC) uses applicable simulation equations for the aerodynamic performance of the TPS in their flight simulator and data reduction program (HEATSET). The approach was to use the HEATSET program to determine the heating an one critical point on the body flap during the STS-2 entry flight test inputs (Flap Thermocouple V07T9508). From these results and other results on the outboard elevons, the maximum flap deflection angle and Orbiter aft center of gravity could be established. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1982
- Accession Number
- ADA124844
Entities
People
- John Robert Wood
Organizations
- Air Force Institute of Technology