Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction

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Created Date
1969
Description

Includes bibliographical references (p. 16-17).

Dynamic response of supersonic mixed compression inlet coupled to cold pipe or turbojet engine.

Creator

Wasserbauer, Joseph F

Partner
HathiTrust
Contributing Institution
University of Illinois
Publisher
Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151]
Subjects
Supersonic wind tunnels
Wind tunnels
Aerodynamics, Supersonic
Type
text
Format
Language material
Electronic resource
Language
English
URL
http://catalog.hathitrust.org/Record/011444615
Rights
Public domain. Learn more at http://www.hathitrust.org/access_use
Chicago citation style
Wasserbauer, Joseph F. Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction. 1969. Retrieved from the Digital Public Library of America, http://catalog.hathitrust.org/Record/011444615. (Accessed April 19, 2024.)
APA citation style
Wasserbauer, Joseph F, (1969) Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction. Retrieved from the Digital Public Library of America, http://catalog.hathitrust.org/Record/011444615
MLA citation style
Wasserbauer, Joseph F. Retrieved from the Digital Public Library of America <http://catalog.hathitrust.org/Record/011444615>.
Note: These citations are programmatically generated and may be incomplete.