Download or read book An Experimental Study of Boundary Layer Transition on a Caret Wing at Hypersonic Speeds written by Ramakant Bhojra Deshpande and published by . This book was released on 1968 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Studies on Boundary layer Transition on a Reentry Vehicle of Transonic and Supersonic Speeds written by Kojiro Suzuki and published by . This book was released on 1995 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: The boundary-layer transition on the EXPRESS reentry capsule at transonic and supersonic speeds is studied experimentally by the wind tunnel tests. For the diagnostic of the turbulent transition of the boundary-layer, the China-clay method is used. The experimental results clarify that when the freestream Mach number increases, the transition point moves downstream on the body surface and the distance between the beginning of the transition and its completion to the fully turbulent flow becomes larger. The effects of the freestream Mach number on the location of the boundary-layer transition are described successfully in terms of two non-dimensional quantities, that is, the transition Reynolds number and the local Mach number at the boundary-layer edge. The oil-flow pictures reveal that in the transonic regime, the separation bubble is formed at the junction between the blunt nose and the conical part of the body and therefore the transition begins behind the reattachment point of the separation bubble. The effects of the turbulent transition on the aerodynamic characteristics of the reentry body are investigated by using the technique of the boundary-layer trip and the experimental results show that the aerodynamic characteristics of the EXPRESS reentry vehicle are not sensitive to the boundary-layer transition.
Download or read book Pegasus Wing glove Experiment to Document Hypersonic Crossflow Transition written by Arild Bertelrud and published by . This book was released on 2000 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented. A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus® launch vehicle and was flown at speeds of up to Mach 8 and altitudes of up to 250,000 ft. The wing-glove experiment was flown as a secondary payload off the coast of Florida in October 1998. This paper describes the measurement system developed. Samples of the results obtained for different parts of the trajectory are included to show the characteristics and quality of the data. Thermocouples and pressure sensors (including Preston tubes, Stanton tubes, and a "probeless" pressure rake showing boundary layer profiles) measured the time-averaged flow. Surface hot-films and high-frequency pressure transducers measured flow dynamics. Because the vehicle was not recoverable, it was necessary to design a system for real-time onboard processing and transmission. Onboard processing included spectral averaging. The quality and consistency of data obtained was good and met the experiment requirements.
Download or read book Boundary layer Transition Results from the F 16xl 2 Supersonic Laminar Flow Control Experiment written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-27 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 X 10(exp 6), optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.Marshall, Laurie A.Armstrong Flight Research CenterLAMINAR FLOW; LAMINAR BOUNDARY LAYER; BOUNDARY LAYER TRANSITION; BOUNDARY LAYER CONTROL; SUPERSONIC FLOW; SUCTION; CIVIL AVIATION; SUPERSONIC SPEED; ALTITUDE; MACH NUMBER; SWEPT WINGS; F-16 AIRCRAFT; PRESSURE DISTRIBUTION...
Download or read book Boundary Layer Transition in the Leading Edge Region of a Swept Cylinder in High Speed Flow written by Colin Phillip Coleman and published by . This book was released on 1998 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Effects of Leading edge Sweep on Boundary layer Transition at Supersonic Speeds written by Gary T. Chapman and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Boundary layer Transition on X 15 2 Research Airplane written by Albert L. Braslow and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Boundary Layer Transition Mapping at Supersonic Speeds Measured by Liquid Crystals written by and published by . This book was released on 1973 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to evaluate the use of encapsulated liquid crystals as a means of mapping boundary layer transition patterns on delta wings. Since the method relies solely on surface temperature changes, one must be sure that boundary layer transition is in fact the cause for the change. Where temperature gradients caused by inviscid effects occur, there can be difficulty in isolating the true transition pattern from other effects. By varying unit Reynolds number, the temperature/color pattern associated with transition marches forward (or aft) while inviscid related patterns retrain fixed. In most cases this mechanism is sufficient to separate the effects.
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.
Download or read book Boundary Layer Transition on a Generic Model of Control Flaps in Hypersonic Flow written by Madlen Leinemann and published by . This book was released on 2022-06-29 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the present thesis, experimental and numerical investigations were performed to study boundary layer transition on a generic model of a control surface in hypersonic flow at Mach 6. Experiments were carried out in the Hypersonic Ludwieg Tube at TU Braunschweig (HLB) and in the BAM6QT at Purdue University. In order to investigate the influence of the deflection angle, the Reynolds number and the leading edge radius, flow visualizations (Schlieren), pressure and heat transfer measurements were applied. In the BAM6QT at Purdue University, experiments were carried out under noisy and quiet flow conditions to allow investigations on the influence of the free stream conditions. It was found, that particularly the leading edge bluntness has a great impact on the recirculation region. For the investigated nose radii of rn = 30μm - 330μm, a strong increase of the separation bubble size was observed for increasing nose bluntness. Numerical investigations were performed based on RANS equations. For the HLB measurements, experimental data in combination with stability analysis revealed the presence of second mode instabilities on the cylinder section in the attached boundary layer. Within the flow separation, a shift in frequency was observed to a frequency range typical for first mode instabilities. Due to the lack of a numerical stability analysis for oblique waves the presence of first modes can not be proven. In the Purdue measurements, second modes could not be observed.
Download or read book NASA SP written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Brief Review of Some Mechanisms Causing Boundary Layer Transition at High Speeds written by and published by . This book was released on 1990 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Theoretical and Experimental Study of the Boundary Layer Flow on a 45 Swept Back Wing written by F. M. Burrows and published by . This book was released on 1956 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Summary of Laminar Boundary Layer Control Research written by Northrop Corporation Boundary Layer Research Section and published by . This book was released on 1964 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt: At subsonic speeds, full length laminar flow and low drags were obtained up to high length Reynolds numbers on a thin straight, on a swept laminar suction wing and on a suction body of revolution. Moderately increased suction rates in the most critical region of a straight and a swept laminar suction wing enabled full chord laminar flow in the presence of external sound. Theoretical investigatiions are concerned with nonlinear boundary layer oscillations and stability investigations (assuming small disturbances) of a supersonic laminar boundary layer on a flat plate up to high supersonic speeds as well as on a highly swept supersonic low drag suction wing of low wave drag. On a supersonic flat laminar suction plate with and without weak incident shock waves, extensive laminar flow and low equivalent drags were obtained at M = 3 up to length Reynolds numbers of 26 x 1000000. Further supersonic low drag suction experiments on a suction body of revolution, on a 36 degree supersonic yawing wing, as well as on a 72 degree supersonic yawing wing (swept behind the Mach cone) of low wave drag, are described. The latter wing showed full chord laminar flow with a subsonic type pressure distribution at M = 2 and R sub C approximately equal to 1000000. (Author).
Download or read book Addendum to a Theoretical and Experimental Study of the Boundary Layer Flow on a 45 Swept Back Wing written by J. Walton and published by . This book was released on 1957 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Laminar Transitional and Turbulent Boundary layer Profiles on a Wedge at Local Mach Number 6 5 and Comparisons with Theory written by Michael C. Fischer and published by . This book was released on 1971 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel investigation of laminar, transitional, and turbulent boundary layer profiles on wedge at hypersonic speed to confirm theoretical analysis.
Download or read book Boundary layer Transition Under Hypersonic Conditions written by J. Leith Potter and published by . This book was released on 1965 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
