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Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90° / by Jim A. Penland.

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Format:
Book
Government document
Author/Creator:
Penland, Jim A., author.
Contributor:
United States. National Advisory Committee for Aeronautics, issuing body.
Series:
Technical note (United States. National Advisory Committee for Aeronautics) ; 3861.
Technical notes / National Advisory Committee for Aeronautics ; No. 3861
Language:
English
Subjects (All):
Cylinders--Aerodynamics.
Cylinders.
Aerodynamic load.
Wind tunnel testing.
Hypersonic wind tunnels.
Physical Description:
1 online resource (32 pages) : illustrations.
Other Title:
Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to ninety degrees
Place of Publication:
Washington, [D.C.] : National Advisory Committee for Aeronautics, 1957.
Summary:
Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
Notes:
Title from title screen (viewed March 7, 2019).
"January 1957."
"Langley Aeronautical Laboratory, Langley Field, Va."
"Supersedes recently declassified NACA Research Memorandum L54A14 by Jim A. Penland, 1954"--Page 1.
No Federal Depository Library Program (FDLP) item number.
Includes bibliographical references (page 13-14).
Electronic reproduction. Denton, Texas : University of North Texas, 2011 Electronic reproduction from print master produced by University of North Texas
Other Format:
Print version: Penland, Jim A., Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees
OCLC:
1100474464

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