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An investigation of unsteady pressure and temperature characteristics due to shock-boundary layer interactions in a mach 6 axisymmetric flowfield

机译：马赫6轴对称流场中由于冲击边界层相互作用而引起的非稳态压力和温度特性的研究

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作者
Flanagan, Michael John, Jr.;
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作者单位

The Ohio State University;

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授予单位 The Ohio State University;
学科
学位 Ph.D.
年度 1991
页码 167 p.
总页数 167
原文格式 PDF
正文语种 eng
中图分类
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1. Study of unsteady characteristics of flare-induced hypersonic shock-wave boundary-layer interaction flowfield with variation in γ [J] . S. B. Verma The Aeronautical Journal . 2003,第1069期

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2. Unsteady Characteristics of a Swept-Shock/Boundary-Layer Interaction at Mach 2 [J] . Arora Nishul, Mears Lee, Alvi Farrukh S. AIAA Journal . 2019,第10期

机译：2马赫扫掠/边界层相互作用的非稳态特征
3. Investigations on flowfield behavior and resistance backpressure characteristics of supersonic cascade with boundary layer suction [J] . Wang Ziao, Chang Juntao, Zhang Junlong, Acta astronautica . 2018,第NOVa期

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4. Unsteady Surface and Flowfield Measurements in Ramp-Induced Turbulent and Transitional Shock-Wave Boundary-Layer Interactions at Mach 6 [C] . Thomas Whalen, Richard Kennedy, Stuart Laurence, AIAA SciTech forum and exposition . 2019

机译：在6马赫速度下引起的湍流和过渡冲击波边界层相互作用中的非稳态表面和流场测量
5. Flowfield of a Three-dimensional Swept-shock Boundary Layer Interaction at Mach 2 [D] . Arora, Nishul. 2018

机译：2马赫数二维扫频边界层相互作用的流场
6. The Effects of Thermal Radiation on an Unsteady MHD Axisymmetric Stagnation-Point Flow over a Shrinking Sheet in Presence of Temperature Dependent Thermal Conductivity with Navier Slip [O] . Sabyasachi Mondal, Nageeb A. H. Haroun, Precious Sibanda -1

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7. D2.3 - Numerical Investigation of Unsteady Flowfield of DN25 Flow Meter with Pressure Chamber [O] . A. Gedikli, H. Krisch, E. von Lavante 2013

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8. Exploratory Investigation of the Effects of Boundary-Layer Control on the Pressure-Recovery Characteristics of a Circular Internal-Contraction Inlet with Translating Centerbody at Mach Numbers of 2.00 and 2.35 [R] . Martin, Norman J. 1959

机译：边界层控制对转子中心体圆形内收缩入口压力恢复特性影响的探索性研究，马赫数为2.00和2.35

An investigation of unsteady pressure and temperature characteristics due to shock-boundary layer interactions in a mach 6 axisymmetric flowfield

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