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Nose Tip Recession Measuring System for Hypersonic Test Vehicles

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Date Issued:
1977
Abstract/Description:
Florida Technological University College of Engineering Thesis; A method is presented which permits the measure of nose tip recession of re-entry vehicles and advanced terminal interceptors by employing a double choked flow coolant gas system. Recession of the tip results in an increased exit flow area which reduces the total pressure of the gas in the blast tube. Measurement of the blast tube pressure and gas generator (chamber) pressure will produce an effective measurement of the nose tip recession as long as choked flow (i.e., sonic velocity) is maintained in both the tip exit area and the gas' generator throat area. Governing flow equations documented in the literature are developed for double choked flow. Hypersonic wind tunnel test data are presented to verify the developed flow equations and to identify the mass flow ratios necessary to sustain double choked flow.
Title: Nose Tip Recession Measuring System for Hypersonic Test Vehicles.
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Name(s): Brown, James Anthony, Author
Evans, Ronald D., Committee Chair
Engineering, Degree Grantor
Type of Resource: text
Date Issued: 1977
Publisher: Florida Technological University
Language(s): English
Abstract/Description: Florida Technological University College of Engineering Thesis; A method is presented which permits the measure of nose tip recession of re-entry vehicles and advanced terminal interceptors by employing a double choked flow coolant gas system. Recession of the tip results in an increased exit flow area which reduces the total pressure of the gas in the blast tube. Measurement of the blast tube pressure and gas generator (chamber) pressure will produce an effective measurement of the nose tip recession as long as choked flow (i.e., sonic velocity) is maintained in both the tip exit area and the gas' generator throat area. Governing flow equations documented in the literature are developed for double choked flow. Hypersonic wind tunnel test data are presented to verify the developed flow equations and to identify the mass flow ratios necessary to sustain double choked flow.
Identifier: CFR0003483 (IID), ucf:53031 (fedora)
Note(s): 1977-01-01
M.S.
Engineering
Masters
This record was generated from author submitted information.
Electronically reproduced by the University of Central Florida from a book held in the John C. Hitt Library at the University of Central Florida, Orlando.
Subject(s): Guided missiles -- Design and construction
Persistent Link to This Record: http://purl.flvc.org/ucf/fd/CFR0003483
Restrictions on Access: public
Host Institution: UCF

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