Operating Characteristics of the AFAPL Hypersonic Shock Tunnel.
Abstract
A description is presented of the development efforts accomplished to make the AFAPL Hypersonic Shock Tunnel an operational aerodynamic facility. A semiconductor strain gage pressure transducer was developed to overcome calibration problems with the original pressure transducer design. Heat transfer measurements were initially made using standard shock tunnel thin film gage technology. Gage erosion problems were solved through use of a surface thermocouple which uses n-p germanium crystal elements. Improved data recording capability was achieved with the installation of a 64 channel digital data system. A contoured nozzle with interchangeable throats to provide parallel uniform flows at Mach 8, 9, 10, and 11 was installed and calibrated. The nozzle produced good flow profiles up to six feet from the nozzle exit. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1970
- Accession Number
- AD0715907
Entities
People
- R. R. Craig
Organizations
- Air Force Research Laboratory