超高速大气飞行和超燃冲压发动机燃烧室条件下气体动力学参数在风洞中正确全尺寸重现的背景和预测

V.I. Alfyorov, L.M. Dmitriyev, B.V. Yegorov, Yu.Ye. Markachev, A. Rudakova
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引用次数: 1

摘要

该报告分析了用于再现气体动态参数(速度、密度、压力和温度)和化学空气成分的气动钻机的可能方案,并指出了所需的停滞参数(P/sub 0/, T/sub 0/)。通过对经典设施喷嘴内发生的物理化学过程的计算,推断出即使在解决在超高温度和压力(T/sub / 0//spl ges/7000 K, P/sub / 0//spl ges/4/spl middot/10/sup 8/ Pa)下在充气室内产生和保持气体的问题时,化学空气组成也与自然空气组成有明显的不同。分析表明,mhd气体加速装置在解决上述问题方面具有明显的优势。给出了一套磁气动力学和多温度物理化学动力学方程,作为计算程序的基础。考虑了不同气体密度下能量从电磁场向气体的输运通道。该程序是利用在TsAGI mhd -气体加速高超声速风洞中获得的实验数据编制的。该报告提供了在广泛的初始条件和电动力学参数下气体加速机制的计算数据。考虑到mhd通道和二次喷嘴中的非平衡物理化学过程,可以说明非平衡效应在很大程度上促进了设备测试段中自然化学空气成分和静态温度的再现。研究了碱种子对超燃冲压发动机燃烧室内诱导时间和氢燃烧过程的影响。分析了实现mhd加速器计算版的可能技术途径。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Background and prediction of correct full-scale reproduction in wind tunnels as concerns gas dynamic parameters of hypervelocity atmospheric flights and scramjet combustion chamber conditions
The report analyzes possible schemes of aerodynamic rigs intended for reproducing gas dynamic parameters (velocity, density, pressure, and temperature) and chemical air composition as applied to the TAV trajectory with the indication of required stagnation parameters (P/sub 0/, T/sub 0/). Based on the calculation of physico-chemical processes taking place in nozzles of classical facilities it is inferred that the chemical air composition differs noticeably from the natural air composition even in solving the problem of producing and retaining the gas in the plenum chamber at ultrahigh temperatures and pressures (T/sub 0//spl ges/7000 K, P/sub 0//spl ges/4/spl middot/10/sup 8/ Pa). The analysis carried out reveals a distinct advantage of MHD-gas acceleration facilities in solving the stated problem. A set of equations of magnetogasdynamics and multitemperature physico-chemical kinetics which underlie the computation program is presented. The channels of energy transport from the electromagnetic field to the gas at different gas densities are considered. The program was compiled using the experimental data obtained in the TsAGI MHD-gas acceleration hypersonic wind tunnel. The report presents the calculated data on gas acceleration regimes in a wide spectrum of initial conditions and electrodynamic parameters. The consideration of nonequilibrium physico-chemical processes in the MHD-channel and in the secondary nozzle makes it possible to state that the nonequilibrium effects facilitate considerably the reproduction of a natural chemical air composition and a static temperature in the facility test section. The influence of alkali seeds on the induction time and hydrogen burning process in the scramjet combustion chamber is evaluated. Possible technical approaches to the realization of calculated versions of MHD-accelerators are analyzed.
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