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Design criteria for axisymmetric and two-dimensional supersonic inlets and exits
- Author / Creator
- Available as
- Online
- Summary
-
For Mach numbers up to 4.0, design charts are presented for single and double-oblique-shock inlets and for isentropic axisymmetric and two-dimensional surfaces having theoretically focused Mach lin...
For Mach numbers up to 4.0, design charts are presented for single and double-oblique-shock inlets and for isentropic axisymmetric and two-dimensional surfaces having theoretically focused Mach lines. Nondimensional geometric contours with corresponding local Mach number and flow-angle variations are presented for a systematic family of isentropic surfaces for Mach numbers from 2.0 to 4.0 in increments of 0.25. All solutions are carried from the free-stream Mach number to a local Mach number of unity and are applicable for use in the design of either inlets or exhaust nozzles.
Details
- Creator
- by James F. Connors and Rudolph C. Meyer
- Included Title
-
- Technical Report Archive & Image Library (TRAIL)
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1956
- Physical Details
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- 1 online resource (42 pages) : illustrations, tables
- OCLC
- on1386275643
- Date of issue: January 1956.
- Report no. NACA-TN-3589.
- "Lewis Flight Propulsion Laboratory."
- Title from title screen (viewed June 23, 2023)
- Includes bibliographical references (page 12)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.