Compressible gas flow tables for specific heat ratio (γ) = 4/3 (Mach number 0.000 to 2.000)

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DOI	Resolve DOI: https://doi.org/10.4224/40003682
Author	Search for: Bassett, R. W.¹; Search for: Chappell, M. S.¹
Affiliation	National Research Council Canada. Division of Mechanical Engineering
Format	Text, Technical Report
Physical description	49 p.
Abstract	The isentropic ratios usually used in compressible gas flow calculations are tabulated for a specific heat ratio (γ) of 4/3 and Mach numbers ranging from 0. 000 to 2. 000 in increments of 0. 001. The values tabulated include: pressure ratio, temperature ratio, area ratio, non-dimensional mass flow with respect to total pressure, non-dimensional mass flow with respect to static pressure, and velocity divided by the square root of the total temperature. Because of the general applicability of these tables to various propulsion calculations , they have been published as an Aeronautical Report.
Publication date	1962-01
Publisher	National Research Council Canada
Series	Aeronautical Report (National Research Council Canada. Division of Mechanical Engineering. Engine Laboratory), no. LR-324 (January 1962).
Language	English
Peer reviewed	No
NRC number	NRCC-0006769 NRC-6769
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Record identifier	e0d87632-0f22-4ff3-ad1a-a76fe88b75de
Record created	2025-09-03
Record modified	2025-11-03