The work presented within compares the wind readings obtained from a weapon mountable hot wire anemometer and co-located down range laser wind sensor to the data collected from a string of propeller and vane anemometers set up along a firing line. The purpose of this effort was to determine if a combination of the two sensors would be able to measure the wind conditions a projectile would be subject to along its flight path to a target. The results of the work showed that the sensor suite was...
Topics: DTIC Archive, Bober,Tomas R, ARDEC Picatinny Arsenal United States, fire control systems, hot wire...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
The mechanism of turbulence production is identified. Simultaneous flow visualization and hot-wire anemometry have been used. A new scaling of the burst rate has been found. (Author)
Topics: DTIC Archive, Falco,Robert E, MICHIGAN STATE UNIV EAST LANSING DEPT OF MECHANICAL ENGINEERING,...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Numerical predictions of turbulent vortex flow in cyclone chambers are made with the aid of a two-equation model of turbulence which entails the solution of elliptic differential equations of the transport of turbulence energy and its dissipation rate. The non-homogeneous and anisotropic nature of turbulence is accounted for by employing a two-viscosity concept. Reasonable agreement is obtained between the calculated axial and tangential velocity profiles and the experimental data available in...
Topics: DTIC Archive, Boysan, F, SHEFFIELD UNIV (UNITED KINGDOM) DEPT OF CHEMICAL ENGINEERING AND FUEL...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel (A) (at Mach numbers 1.5, 2, 3, 4, and 5) and in the 50-in. Hypersonic Tunnel (B) (at Mach numbers 6 and 8) of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling...
Topics: DTIC Archive, Strike, W T , Jr, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
Measurements are presented of vortex shedding frequencies for circular cylinders in confined flows. Experiments have been performed at Reynolds numbers up to 20,000. The range of blockage ratios covered was 0.18-0.33. Systematic changes in the shedding frequency were observed with increasing blockage, the effect being greatest at Reynolds numbers of a few thousand. Measurements of the Reynolds number for which vortex shedding just begins show that the confining walls increase the stability of...
Topics: DTIC Archive, Rees,W G, CAMBRIDGE UNIV (ENGLAND) CAVENDISH LAB, *VORTEX SHEDDING, *FLOW SEPARATION,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, *SURFACE ROUGHNESS, *TURBULENT BOUNDARY LAYER, *BOUNDARY LAYER FLOW, TURBULENCE, FLOW...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, Schofield,W H, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS,...
The development of a turbulent boundary layer flow through a gap in an isolated wall-mounted roughness element has been studied experimentally. Two flow regions were distinguished downstream of the gap; a distortion region followed by a readjustment region. In the distortion region two counteracting distortion mechanisms were identified, the relative importance of which depended on gap size. Thus flows downstream of large gaps were found to differ significantly from those through small gaps....
Topics: DTIC Archive, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *SURFACE ROUGHNESS, *TURBULENT...
This report gives details of how to use the constant-temperature hot-wire-anemometer system at DST Group to measure mean velocities, broadband turbulence terms and spectra of velocity fluctuations in the low-speed wind tunnel at DST Group. The use of both single-wire and crossed-wire (2 wire) probes is described. Areas covered include a description of the anemometers and probes, soldering hot-wire filaments onto the prongs of a probe, etching the filaments, setting up of instrumentation,...
Topics: DTIC Archive, Erm,Lincoln P, DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION FISHERMANS BEND...
