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Investigation Of Boundary Layer Transition In Hypersonic Flow At Angle Of Attack
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Book Synopsis Investigation of Boundary Layer Transition in Hypersonic Flow at Angle of Attack by : A. L. Nagel
Download or read book Investigation of Boundary Layer Transition in Hypersonic Flow at Angle of Attack written by A. L. Nagel and published by . This book was released on 1966 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical and experimental investigation has been made of boundary layer transition at angle of attack in hypersonic flow. A new method of calculating laminar flow stability has been developed that is more general than previous methods. The method employs the timewise integration of perturbation equations derived from the complete Navier-Stokes equations for two-dimensional flow of a compressible fluid with variable transport properties. The present calculations are for perturbations about a known steady flow. The perturbations are assumed to be sinusoidal in the streamwise direction, but no restriction is known that would prevent the streamwise wave form from being arbitrary, as are the vertical distributions and the time variations. The sinusoidal wave assumption greatly reduces the amount of computer time required and simplifies the interpretation of the results. Nonlinear terms are easily retained with the present method, but nonlinear calculations are not physically correct when perturbations are required to be sinusoidal. For this reason, nonlinear terms were deleted for all calculations presented. The experimental program was conducted at Mach numbers of 6, 8, and 10. The models included blunt and sharp flat plates and a 75-degree swept delta wing with sharp leading edges.
Book Synopsis Transition Fixing for Hypersonic Flow by :
Download or read book Transition Fixing for Hypersonic Flow written by and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comments on Hypersonic Boundary-layer Transition by : Kenneth F. Stetson
Download or read book Comments on Hypersonic Boundary-layer Transition written by Kenneth F. Stetson and published by . This book was released on 1990 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
Book Synopsis Roughness, Bluntness, and Angle of Attack Effects on Hypersonic Boundary Layer Transition by : H. T. Nagamatsu
Download or read book Roughness, Bluntness, and Angle of Attack Effects on Hypersonic Boundary Layer Transition written by H. T. Nagamatsu and published by . This book was released on 1964 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in a hypersonic shock tunnel to study the laminar boundary layer transition on a highly cooled 10-degree cone of 4-foot length over the Mach number range of 8.5 to 10.5 with a stagnation temperature of 1400K. The effects on transition of tip surface roughness, tip bluntness, and =2-degree angle of attack were investigated. With fast response thin film surface heat transfer gauges, it was possible to detect the passage of turbulent bursts that appeared at the beginning of transition. It was found that the surface roughness greatly promoted transition in the proper Reynolds number range. The Reynolds number for the beginning and end of transition at the 8.5 Mach number location were 3,800,000 to 9,600,000 and 2,200,000 to 4,200,000 for the smooth sharp tip and rough sharp tip, respectively. The local skin friction data agreed with the heat transfer data through Reynolds analogy. The tip bluntness data showed a strong delay in the beginning of transition for a cone base to tip diameter ratio of 20, approximately a 35% increase in Reynolds number over that of the smooth sharp tip case. The angle of attack data indicated the cross flow to have a strong influence on transition by promoting it on the sheltered side of the cone and delaying it on the windward side. (Author).
Book Synopsis Boundary Layer Transition and Surface Roughness Effects in Hypersonic Flow by : Michael S. Holden
Download or read book Boundary Layer Transition and Surface Roughness Effects in Hypersonic Flow written by Michael S. Holden and published by . This book was released on 1981 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Aerodynamic Characteristics of Slender Hypersonic Vehicles at High Angles of Attack by : Robert H. Feldhuhn
Download or read book An Experimental Investigation of the Aerodynamic Characteristics of Slender Hypersonic Vehicles at High Angles of Attack written by Robert H. Feldhuhn and published by . This book was released on 1968 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Book Synopsis Hypersonic Boundary Layer Transition Experiments by :
Download or read book Hypersonic Boundary Layer Transition Experiments written by and published by . This book was released on 1980 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: New hypersonic wind tunnel data have been obtained to investigate boundary layer transition, with primary emphasis given to tip bluntness and angle of attack effects. The rearward displacement of transition on the cone frustum due to tip bluntness was found to be quite sensitive to free stream Mach number as well as the entropy layer swallowing by the boundary layer. At the highest Mach number obtained in these experiments (M = 9.3), the length of laminar flow could be extended to about nine times the length of laminar flow of a sharp cone at identical conditions. The sensitivity of the maximum rearward displacement of transition with free stream Mach number appeared to be primarily related to local Reynolds number reduction because of pressure losses across the bow shock. Low transition Reynolds numbers typically found on nosetips, extended onto the front portion of the cone frustum. It appears that the still unexplained low transition Reynolds numbers associated with blunt bodies in hypersonic flow includes not only the nosetip region, but the forward portion of the cone frustum. Transition location was found to be sensitive to small changes in angle of attack, and both the sharp and blunt tips produced a rearward movement of transition on the windward ray at small angles of attack. A low supersonic flared nozzle closely duplicated the hypersonic pressure and heat transfer distributions over the nose region of a blunt body.
Book Synopsis Experimental Investigation of Boundary-layer Transition on a Cooled 7.5° Total-angle Cone at Mach 10 by : Philip E. Everhart
Download or read book Experimental Investigation of Boundary-layer Transition on a Cooled 7.5° Total-angle Cone at Mach 10 written by Philip E. Everhart and published by . This book was released on 1967 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Supersonic Boundary Layer Transition and Turbulent Structure by : Alexander J. Smits
Download or read book Investigation of Supersonic Boundary Layer Transition and Turbulent Structure written by Alexander J. Smits and published by . This book was released on 1990 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies by : James E. Brunk
Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
Book Synopsis Flow-field and Drag Characteristics of Several Boundary-layer Tripping Elements in Hypersonic Flow by : Allen H. Whitehead (Jr.)
Download or read book Flow-field and Drag Characteristics of Several Boundary-layer Tripping Elements in Hypersonic Flow written by Allen H. Whitehead (Jr.) and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flow field and drag characteristics of several laminar boundary layer tripping element in hypersonic flow.
Book Synopsis Studies of Hypersonic Boundary Layer Behavior by : A. J. Smits
Download or read book Studies of Hypersonic Boundary Layer Behavior written by A. J. Smits and published by . This book was released on 1995 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary Layer Effects by : Anthony W. Fiore
Download or read book Boundary Layer Effects written by Anthony W. Fiore and published by . This book was released on 1978 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.
Book Synopsis Viscous Flow Interaction Studies by : Robert H. Korkegi
Download or read book Viscous Flow Interaction Studies written by Robert H. Korkegi and published by . This book was released on 1975 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research was designed to gain understanding of the flow of air at high speeds over the components of lifting supersonic and hypersonic vehicles--wings, flaps, fins, inlets--and their interactions with respect to heating, surface friction, pressure, and aerodynamic forces. The objective was to help predict (a) flows on complex aerospace vehicle configurations in high-speed flight and (b) the location of areas of high heating. The research covers the areas of laminar and turbulent boundary layers, boundary layer transition, boundary layer separation, base flows and wakes, low density flows, three-dimensional interactions, viscous flow problems, and some flow measurement techniques.
Book Synopsis Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows by : Marvin I. Kussoy
Download or read book Documentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows written by Marvin I. Kussoy and published by . This book was released on 1989 with total page 32 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...
Book Synopsis Factors Affecting Transition at Supersonic Speeds by : K. R. Czarnecki
Download or read book Factors Affecting Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1953 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper surveys the available material and summarizes what is known to date about boundary-layer transition at supersonic speeds. Variables studied include Mach number, Reynolds number, pressure gradients, heat transfer, surface roughness, and angle of attack. The discussion is limited to bodies of revolution because similar reliable data for wings is lacking.
