Accession Number : AD0715907
Title : Operating Characteristics of the AFAPL Hypersonic Shock Tunnel.
Descriptive Note : Technical rept. Jun 66-Feb 69,
Corporate Author : AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
Personal Author(s) : Craig,R. R.
Report Date : AUG 1970
Pagination or Media Count : 39
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)
Descriptors : (*SHOCK TUBES, PERFORMANCE(ENGINEERING)), STRAIN GAGES, TRANSDUCERS, HYPERSONIC FLOW, CALIBRATION, HEAT TRANSFER, NOZZLE THROATS, NOZZLE GAS FLOW
Subject Categories : Aerodynamics
Test Facilities, Equipment and Methods
Distribution Statement : APPROVED FOR PUBLIC RELEASE