By G. Klingenberg, J. Knapton, W. Morrison, G. Wren
This article seeks to supply a entire and systematic up to date remedy of liquid propellant gun expertise. The booklet discusses early ways to gun layout, equivalent to bulk-loaded configurations and using regeneratively injected bipropellants, via very contemporary advancements within the box of large-calibre and electrothermal-chemical structures. moreover, hybrid and electrothermal propulsion platforms are lined within the textual content, as are smooth ways to electrical gun improvement similar to electrothermal gun know-how. This e-book is meant for pro engineers and scientists within the fields of gun propulsion, ballistics and combustion, and for physicists, chemists and scholars - undergraduate via postgraduates - drawn to those fields. the most target of the e-book is to explain, extensive, the result of quite a few experimental and theoretical learn from 1950 until eventually the current within the box of liquid propellant propulsion. Even this present day, many of the info touching on liquid propellant gun examine continues to be scattered between army, foreign and personal documents. One advantage of utilizing this article is that the reader can locate info, formerly to be had merely via many resources, synthesized in a single booklet.
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Eq. (20) is a convenient way to couple the solution of the mixing length to the flowfield. In the wake-law region of the boundary layer, locally defined eddy diffusivity is commonly used. For example, Purchased from American Institute of Aeronautics and Astronautics 34 W. E. NICOLET AND A. BALAKRISHNAN Kendall et al. 018 u e 6^ (21 where oo r I \ " uMdy (22 2 is the incompressible displacement thickness. Moss also employs locally defined eddy viscosities in his calculations of hypervelocity entry flows.
June 4-6, 1979. , 1979. All rights reserved. *Member, Technical Council, Aerospace Systems Division. Presently, president of Thermal Sciences, Inc. tStaff Engineer, Aerospace Systems Division. 26 Purchased from American Institute of Aeronautics and Astronautics PREDICTING OFF-STAGNATION-POINT FLOWFIELDS 5T = normalized turbulent mixing length, £a*/y Le = Lewis Number p = parameter used in evaluating nonsimilar integrals P = pressure P = parameter defined by Eq. (34) Pr = Prandtl Number Prv = turbulent Prandtl Number q^a = diffusive heat flux qf = radiative heat flux r = local body radius in a meridian plane R Re = radius of curvature = Reynolds Number A s = surface parallel coordinate Sc = Schmidt Number, p/yD Sc.
The important physical events encountered during planetary entry are significantly different from those met during Earth reentry. In particular, the shock-layer radiation causes massive ablation from the w a l l , which affects the entire flowfield; the viscous/mixing region assumes the character of a free shear/mixing region instead of a boundary layer. This requires a significantly different modeling approach. Transition and turbulence also are important since they change the character of the mixing layer and, consequently, the radiation flux reaching the wall.