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- dimenslonal 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.