Ideal-Gas Tables for Oblique-Shock Flow Parameters in Air at Mach Numbers from 1.05 to 12.0

reportActive / Technical Report | Accession Number: ADA397068 | Open PDF

Abstract:

Oblique-shock tables are presented for air with initial Mach numbers from 1.05 to 12.0 and flow-deflection angles from 0 degrees up to the maximum turning angle for attached flow. Parameters presented are flow-deflection angle, shock-wave angle, total-pressure ratio, static-pressure, density, and temperature ratios, downstream Mach number, ratio of downstream velocity to maximum velocity, and increase in entropy. Perfect-gas equations have been used throughout these calculations.

Author(s):
Dennard, John S. ; Spencer, Patricia B.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER
Descriptive Note:
Technical note rept.
Pagination:
0157

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NASA-L-TN-D-2221
Monitor Series:
NASA
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Modernization Areas:
Fully Networked C3
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*SUPERSONIC FLOW, SHOCK WAVES, AIR FLOW, COMPRESSIBLE FLOW, TABLES(DATA), MACH NUMBER, AERODYNAMICS
Field(s)/Group(s):
Fluid Mechanics
Keyword(s):
LOVELACE FOUNDATION COLLECTION
Report Date:
1964 Mar 01
Creation Date:
2001 Dec 26