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Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel

机译：马赫6轴对称隧道中墙体边界层的初步调查

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Temperature and pressure distributions in boundary layer of hypervelocity flow in straight pipe test section

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作者
Feller, W. V.; Jones, R. A.;
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年度 1970
页码 1-71
总页数 71
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
HYPERVELOCITY FLOW; PIPE FLOW; TEMPERATURE DISTRIBUTION; TURBULENT BOUNDARY LAYER; WALL TEMPERATURE; REYNOLDS NUMBER; STAGNATION POINT;

机译：超级流量;管道流量;温度分布;湍流边界层;壁温; REYNOLDs NUmBER; sTaGNaTION pOINT;
入库时间 2022-08-29 11:14:31

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2. Investigation of Laminar-Turbulent Transition in Supersonic Boundary Layers in an Axisymmetric Aerophysical Flight Complex and in a Model in a Wind Tunnel in the Presence of Heat Transfer and Suction of Air [J] . A. I. Leontiev, A. M. Pavlyuchenko High temperature: English translation of teplofizika vysokikh temperatur . 2008,第4期

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3. Numerical simulations of turbulent spots in supersonic boundary layers: Effects of Mach number and wall temperature [J] . J.A. Redford, N.D. Sandham, G.T. Roberts Progress in Aerospace Sciences . 2012,第JULa期

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4. Forced Boundary- Layer Transition of Axisymmetric Inlet in Mach 8 Gun Wind Tunnel and Its Numerical Verification [C] . X. Fan, S. Yi, D. Jia, AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit . 2005

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5. An investigation of unsteady pressure and temperature characteristics due to shock-boundary layer interactions in a mach 6 axisymmetric flowfield [D] . Flanagan, Michael John, Jr. 1991

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6. Analytic Approximate Solutions to the Boundary Layer Flow Equation over a Stretching Wall with Partial Slip at the Boundary [O] . Remus-Daniel Ene, Vasile Marinca, Bogdan Marinca -1

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7. Wind Tunnel Testing on an Axisymmetric Body at Angles of Attack Part V - Boundary Layer Profile Measurement on an Axisymmetric Body [O] . Jayaraman V 1987

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8. Preliminary Surveys of the Wall Boundary Layer in a Mach 6 Axisymmetric Tunnel [R] . Feller, W. V., Jones, R. A. 1970

机译：马赫6轴对称隧道中边界层的初步研究

Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel

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