Abstract
A comparison between orbiter development flight instrumentation (DFI) forward fuselage flight pressure data, obtained from OV-102 during the space transportation system's (STS-1) re-entry, and ground facility and computational results is presented. Wind-tunnel data were obtained on a 0.04-scale orbiter forebody model. Computational data were obtained from the high alpha inviscid solutions (HALIS) computer code. These comparisons will be used to validate the existing experimental data base and optimize pressure modeling techniques developed in support of the Shuttle entry air data system (SEADS). The SEADS is a proposed acrossthe-speed-range second-generation air data system for the orbiter, using an array of flush pressure taps to be installed in the orbiter nose cap and forward fuselage. Knowledge derived from these comparisons will contribute to an improved capability to predict the performance of existing flight systems as well as an improved capability to design space transportation and general flight systems.
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