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Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack up to 90 Degrees

Author:
Penland, Jim A
Published:
January 1957.
Physical Description:
1 electronic document
Online Version

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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.
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19930084664.
Accession ID: 93R13954.
NACA-TN-3861.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15433139