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A Quiet Tunnel Investigation Of Hypersonic Boundary Layer Stability Over A Cooled Flared Cone
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Book Synopsis A Quiet Tunnel Investigation of Hypersonic Boundary-Layer Stability Over a Cooled, Flared Cone by : National Aeronautics and Space Administration NASA
Download or read book A Quiet Tunnel Investigation of Hypersonic Boundary-Layer Stability Over a Cooled, Flared Cone written by National Aeronautics and Space Administration NASA and published by . This book was released on 2018-10-23 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flared-cone model under adiabatic and cooled-wall conditions was placed in a calibrated, low-disturbance Mach 6 flow and the stability of the boundary layer was investigated using a prototype constant-voltage anemometer. The results were compared with linear-stability theory predictions and good agreement was found in the prediction of second-mode frequencies and growth. In addition, the same 'N = 10' criterion used to predict boundary-layer transition in subsonic, transonic, and supersonic flows under low freestream noise conditions was found to be applicable for the hypersonic flow regime as well. Under cooled-wall conditions, a unique set of spectral data was acquired that documents the linear, nonlinear, and breakdown regions associated with the transition of hypersonic flow under low-noise conditions. Blanchard, Alan E. and Selby, Gregory V. and Wilkinson, Stephen P. Langley Research Center NCC1-180...
Book Synopsis An Experimental Investigation of Wall-Cooling Effects on Hypersonic Boundary-Layer Stability in a Quiet Wind Tunnel by : Alan E. Blanchard
Download or read book An Experimental Investigation of Wall-Cooling Effects on Hypersonic Boundary-Layer Stability in a Quiet Wind Tunnel written by Alan E. Blanchard and published by . This book was released on 1996 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the primary reasons for developing quiet tunnels is for the investigation of high-speed boundary-layer stability and transition phenomena without the transition-promoting effects of acoustic radiation from tunnel walls. In this experiment, a flared-cone model under adiabatic- and cooled-wall conditions was placed in a calibrated, "quiet" Mach 6 flow and the stability of the boundary layer was investigated using a prototype constant-voltage anemometer. The results of this experiment were compared with linear-stability theory predictions and good agreement was found in the prediction of second-mode frequencies and growth. In addition, the same "N = 10" criterion used to predict boundary-layer transition in subsonic, transonic, and supersonic flows was found to be applicable for the hypersonic flow regime as well. Under cooled-wall conditions, a unique set of continuous spectra data was acquired that documents the linear, nonlinear, and breakdown regions associated with the transition of hypersonic flow under low-noise conditions
Book Synopsis Hypersonic Boundary Layer Stability Over a Flared Cone in a Quiet Tunnel by : Jason T. Lachowicz
Download or read book Hypersonic Boundary Layer Stability Over a Flared Cone in a Quiet Tunnel written by Jason T. Lachowicz and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Boundary-Layer Stability Experiments on a Flared-Cone Model at Angle of Attack in a Quiet Wind Tunnel by : National Aeronautics and Space Adm Nasa
Download or read book Hypersonic Boundary-Layer Stability Experiments on a Flared-Cone Model at Angle of Attack in a Quiet Wind Tunnel written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-18 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the effects of angle of attack on hypersonic boundary-layer stability on a flared-cone model was conducted in the low-disturbance Mach-6 Nozzle-Test Chamber Facility at NASA Langley Research Center. This unique facility provided a 'quiet' flow test environment which is well suited for stability experiments because the low levels of freestream 'noise' minimize artificial stimulation of flow-disturbance growth. Surface pressure and temperature measurements documented the adverse-pressure gradient and transition-onset location. Hot-wire anemometry diagnostics were applied to identify the instability mechanisms which lead to transition. In addition, the mean flow over the flared-cone geometry was modeled by laminar Navier-Stokes computations. Results show that the boundary layer becomes more stable on the windward ray and less stable on the leeward ray relative to the zero-degree angle-of-attack case. The second-mode instability dominates the transition process at a zero-degree angle of attack, however, on the windward ray at an angle of attack this mode was completely stabilized. The less-dominant first-mode instability was slightly destabilized on the windward ray. Non-linear mechanisms such as saturation and harmonic generation are identified from the flow-disturbance bispectra. Doggett, Glen P. and Chokani, Ndaona Langley Research Center ANGLE OF ATTACK; AERODYNAMIC NOISE; ZERO ANGLE OF ATTACK; BOUNDARY LAYER STABILITY; HYPERSONIC SPEED; NAVIER-STOKES EQUATION; HYPERSONICS; AERODYNAMIC STABILITY; HYPERSONIC BOUNDARY LAYER; WIND TUNNELS; VELOCITY MEASUREMENT; TEST CHAMBERS; LOW NOISE...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724242556 Total Pages :232 pages Book Rating :4.2/5 (425 download)
Book Synopsis Hypersonic Boundary Layer Stability Experiments in a Quiet Wind Tunnel with Bluntness Effects by : National Aeronautics and Space Administration (NASA)
Download or read book Hypersonic Boundary Layer Stability Experiments in a Quiet Wind Tunnel with Bluntness Effects written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-25 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic boundary layer measurements over a flared cone were conducted in a Mach 6 quiet wind tunnel at a freestream unit Reynolds number of 2.82 million/ft. This Reynolds number provided laminar-to-transitional flow over the cone model in a low-disturbance environment. Four interchangeable nose-tips, including a sharp-tip, were tested. Point measurements with a single hot-wire using a novel constant voltage anemometer were used to measure the boundary layer disturbances. Surface temperature and schlieren measurements were also conducted to characterize the transitional state of the boundary layer and to identify instability modes. Results suggest that second mode disturbances were the most unstable and scaled with the boundary layer thickness. The second mode integrated growth rates compared well with linear stability theory in the linear stability regime. The second mode is responsible for transition onset despite the existence of a second mode subharmonic. The subharmonic disturbance wavelength also scales with the boundary layer thickness. Furthermore, the existence of higher harmonics of the fundamental suggests that nonlinear disturbances are not associated with 'high' free stream disturbance levels. Nose-tip radii greater than 2.7% of the base radius completely stabilized the second mode. Lachowicz, Jason T. and Chokani, Ndaona Langley Research Center NASA-CR-198272, NAS 1.26:198272 NCC1-183; RTOP-505-59-50-02...
Book Synopsis Hypersonic Boundary-Layer Stability Experiments on a Flared-Cone Model at Angle of Attack in a Quiet Wind Tunnel by : Glen P. Doggett
Download or read book Hypersonic Boundary-Layer Stability Experiments on a Flared-Cone Model at Angle of Attack in a Quiet Wind Tunnel written by Glen P. Doggett and published by . This book was released on 1996 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Boundary Layer Stability Experiments in a Quiet Wind Tunnel with Bluntness Effects by : Jason Thomas Lachowicz
Download or read book Hypersonic Boundary Layer Stability Experiments in a Quiet Wind Tunnel with Bluntness Effects written by Jason Thomas Lachowicz and published by . This book was released on 1996 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments by :
Download or read book Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments written by and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational evaluation of two stability experiments conducted in the NASA Langley Mach 6 axisymmetric quiet nozzle test chamber facility is conducted. Navier-Stokes analysis of the mean flow and linear stability theory analysis of boundary layer disturbances is performed in the computations. The effects of adverse pressure gradient and wall cooling are examined. Calculated pressure, temperature and boundary layer thickness distributions show very good overall agreement with experimental measurements. Computed mass flux and total temperature profiles show very good quantitative agreement with uncalibrated hot-wire measurements obtained with the hot-wire operated in high and low overheat modes respectively. Comparisons between calibrated hot-wire data and mean flow computations show excellent agreement in the early stages of the transitional flow. However, examination of the wire Reynolds number and mass flux and total temperature eigenfunction profiles suggest that when operated in high overheat mode the sensitivity of the hot-wire to total temperature is significant. Thus, while uncalibrated hot-wire measurements are useful to characterize the overall features of the flow, calibrated hot-wire measurements are necessary for quantitative comparison with stability theory. Computations show that adverse pressure gradient and wall cooling decrease the boundary layer thickness and increase the frequency and amplification rate of the unstable second mode disturbances; these findings are consistent with the experimental observations.
Book Synopsis A Computational Study of Hypersonic Boundary Layer Stability on a Blunt Nose Flared Cone Model by : Ndaona Chokani
Download or read book A Computational Study of Hypersonic Boundary Layer Stability on a Blunt Nose Flared Cone Model written by Ndaona Chokani and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pharmacotherapeutic in tuberculosis by :
Download or read book Pharmacotherapeutic in tuberculosis written by and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Cooled-Wall Cone in Hypersonic Flows by : J. C. Donaldson
Download or read book Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Cooled-Wall Cone in Hypersonic Flows written by J. C. Donaldson and published by . This book was released on 1988 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of fluctuating flow and mean flow parameters were made in the boundary layer on a cooled wall, sharp 7-deg (half-angle) cone in an investigation of wall temperature effects on the stability of laminar boundary layers in hypersonic flow. The flow fluctuation measurements were made using constant-current hot-wire anemometry techniques. Boundary-layer profiles and cone surface conditions were measured to supplement the hot-wire data. Testing was done at Mach numbers 8 and 6 with a free-stream unit Reynolds number of 1.0-million per foot. The test equipment, test techniques, and the data acquisition and reduction procedures are described. Analysis of the hot wire anemometer data is beyond the scope of this report. Hypersonic flow, Wind tunnel tests, Cold wall model, Boundary layer stability, Hot wire anemometry, Sharp cone. (mjm).
Book Synopsis A Review of Hypersonic Boundary Layer Stability Experiments in a Quiet Mach 6 Wind Tunnel by : Stephen P. Wilkinson
Download or read book A Review of Hypersonic Boundary Layer Stability Experiments in a Quiet Mach 6 Wind Tunnel written by Stephen P. Wilkinson and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments by : Melissa L. Manning
Download or read book Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments written by Melissa L. Manning and published by . This book was released on 2000-11 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational evaluation of two stability experiments conducted in the NASA Langley Mach 6 axisymmetric quiet nozzle test chamber facility is conducted. Navier- Stokes analysis of the mean flow and linear stability theory analysis of boundary layer disturbances is performed in the computations. The effects of adverse pressure gradient and wall cooling are examined. Calculated pressure, temperature and boundary layer thickness distributions show very good overall agreement with experimental measurements. Computed mass flux and total temperature profiles show very good quantitative agreement with uncalibrated hot- wire measurements obtained with the hot-wire operated in high and low overheat modes respectively. Comparisons between calibrated hot-wire data and mean flow computations show excellent agreement in the early stages of the transitional flow. However, examination of the wire Reynolds number and mass flux and total temperature eigenfunction profiles suggest that when operated in high overheat mode the sensitivity of the hot-wire to total temperature is significant. Thus, while uncalibrated hot-wire measurements are useful to characterize the overall features of the flow, calibrated hot- wire measurements are necessary for quantitative comparison with stability theory. Computations show that adverse pressure gradient and wall cooling decrease the boundary layer thickness and increase the frequency and amplification rate of the unstable second mode disturbances; these findings are consistent with the experimental observations.
Book Synopsis Correlations of Supersonic Boundary-layer Transition on Cones Including Effects of Large Axial Variations in Wind-tunnel Noise by : Fang-Jenq Chen
Download or read book Correlations of Supersonic Boundary-layer Transition on Cones Including Effects of Large Axial Variations in Wind-tunnel Noise written by Fang-Jenq Chen and published by . This book was released on 1984 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Boundary-layer Stability on a Flared-cone Model at Angle of Attack by : Glen Patrick Doggett
Download or read book Hypersonic Boundary-layer Stability on a Flared-cone Model at Angle of Attack written by Glen Patrick Doggett and published by . This book was released on 1996 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic-turbulent Boundary-layer Separation Over a Cone-cylinder-flare Configuration by : Arnold Polak
Download or read book Hypersonic-turbulent Boundary-layer Separation Over a Cone-cylinder-flare Configuration written by Arnold Polak and published by . This book was released on 1969 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of a study of hypersonic-turbulent boundary-layer separation over axisymmetric bodies are presented. Pressure, heat-transfer and flow visualization data were obtained for a cone-cylinder-flare configuration. The experimental data were correlated with a theoretical prediction. (Author).
Book Synopsis Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone by : Donald M. Wilson
Download or read book Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone written by Donald M. Wilson and published by . This book was released on 1967 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
