Investigation Of Boundary Layer Reynolds Number For Transition On An Naca 65215 114 Airfoil In The Langley Two Dimensional Low Turbulence Pressure Tunnel
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Effects of Specific Types of Surface Roughness on Boundary-layer Transition
| Author | : Laurence K. Loftin |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1946 |
| Genre | : Aerodynamic load |
| ISBN | : |
Summary: Tests were conducted with two typical low-drag airfoils of 90-inch chord to determine the effects of surface projections, grooves, and sanding scratches on boundary-layer transition. The Reynolds number at which a spanwise row of cylindrical projections would cause premature transition was determined for a range of Reynolds number from approximately 3 x 106 to 10 x 106. Data were obtained for projections of various sizes and chordwise locations on both low-drag airfoils. The results were analyzed on the assumption that the critical airfoil Reynolds number for a given projection was a function only of the local-flow conditions around the projection. This assumption neglected possible effects of tunnel turbulence, pressure gradient, boundary-layer Reynolds number, and the original extent of the laminar flow. The data correlated on the basis of this assumption within a range of critical airfoil Reynolds number of ±0.5 x 106 and within a range of projection height of ±0.002 inch. The tests of surface grooves and sanding scratches indicated that, for the range of Reynolds number investigated, the laminar boundary layer was much less sensitive to surface grooves and sanding scratches than to projections above the surface.
Transition Documentation on a Three-Element High-Lift Configuration at High Reynolds Numbers--Database. Conducted in the Langley Low Turbulence Pressure Tunnel
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 60 |
| Release | : 2018-06-11 |
| Genre | : |
| ISBN | : 9781721029600 |
A 2-D (two dimensional) high-lift system experiment was conducted in August of 1996 in the Low Turbulence Pressure Tunnel at NASA Langley Research Center, Hampton, VA. The purpose of the experiment was to obtain transition measurements on a three element high-lift system for CFD (computational fluid dynamics) code validation studies. A transition database has been created using the data from this experiment. The present report details how the hot-film data and the related pressure data are organized in the database. Data processing codes to access the data in an efficient and reliable manner are described and limited examples are given on how to access the database and store acquired information.Bertelrud, Arild and Johnson, Sherylene and Anders, J. B. (Technical Monitor)Langley Research CenterDATA BASES; HIGH REYNOLDS NUMBER; LIFT; BOUNDARY LAYER TRANSITION; HOT-FILM ANEMOMETERS; COMPUTATIONAL FLUID DYNAMICS; DATA PROCESSING; LOW TURBULENCE
Wind-tunnel Investigation of NACA 66(215)-216, 66,1-212, and 651-212 Airfoils with 0.20-airfoil-chord Split Flaps
| Author | : Felicien F. Fullmer |
| Publisher | : |
| Total Pages | : 22 |
| Release | : 1944 |
| Genre | : Aerodynamics |
| ISBN | : |
Summary: An investigation was carried out in the NACA two-dimensional low-turbulence pressure tunnel of the NACA 66(215)-216, 66,1-212, and 651-212 airfoil sections equipped with split flaps having chords 20 percent of the airfoil chord. The purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps. All the present tests were made at a Reynolds number of approximately 6 x 106 and a Mach number of about 0.15.
Transonic Scaling Effect on a Quasi, Two-dimensional C-141 Airfoil Model
| Author | : C. F. Lo |
| Publisher | : |
| Total Pages | : 74 |
| Release | : 1973 |
| Genre | : Aerofoils |
| ISBN | : |
The transonic scaling effect of shock wave/boundary-layer interaction on a quasi, two-dimensional C-141 airfoil was investigated. Data were obtained from the AEDC Propulsion Wind Tunnel Facility Aerodynamic Wind Tunnel (4T) and Propulsion Wind Tunnel (16T) and from the NASA Marshall Space FLIGHT Center High Reynolds Number Tunnel with 6-in.- and 24-in.-chord airfoils for a range 0.70 to 0.85. In addition to the investigation of the effect of Reynolds number on the airfoil pressure distribution, the effect of fixed boundary-layer transition was evaluated using grit-type transition strips on the airfoil surface. The significant parameters affecting the shock wave/boundary-layer interaction are identified. The data indicate that simulation of higher Reynolds number data on the C-141 airfoil model is feasible by use of a fixed-boundary-layer-transition strip. (Author).
Low Reynolds Number Aerodynamics
| Author | : Thomas J. Mueller |
| Publisher | : Springer Science & Business Media |
| Total Pages | : 456 |
| Release | : 2013-03-08 |
| Genre | : Science |
| ISBN | : 3642840108 |
Current interest in a variety of low Reynolds number applications has focused attention on the design and evaluation of efficient airfoil sections at chord Reynolds numbers from about 100,000 to about 1,000,000. These applications include remotely piloted vehicles (RPVs) at high altitudes, sailplanes, ultra-light man-carrying/man powered aircraft, mini-RPVs at low altitudes and wind turbines/propellers. The purpose of this conference was to bring together those researchers who have been active in areas closely related to this subject. All of the papers presented are research type papers. Main topics are: Airfoil Design and Analysis, Computational Studies, Stability and Transition, Laminar Separation Bubble, Steady and Unsteady Wind Tunnel Experiments and Flight Experiments.
Boundary Layer Effects
| Author | : Anthony W. Fiore |
| Publisher | : |
| Total Pages | : 962 |
| Release | : 1978 |
| Genre | : Turbulent boundary layer |
| ISBN | : |
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.
